EPA-R2-72-052
October 1972 Environmental Protection Technology
Design and Construction
of a System for Remote
Optical Sensing of Emissions
Office of Research and Monitoring
U.S. Environmental Protection Agency
Washington, D.C. 20460
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EPA-R2-72-052
DESIGN AND CONSTRUCTION
OF A SYSTEM FOR REMOTE
OPTICAL SENSING OF
EMISSIONS
by
M. L. Streiff and C. L Claysmith
Convair Aerospace Division of General Dynamics
San Diego, California
Contract No. CPA-22-69-142
Program element No. 1A1010
Project Officer: William F. Herget
Division of Chemistry and Physics
National Environmental Research Center
Research Triangle Park, N. C. 27711
Prepared for
OFFICE OF RESEARCH AND MONITORING
U.S. ENVIRONMENTAL PROTECTION AGENCY
WASHINGTON, D. C. 20460
'"'_." October* 19')2 7 _._. "'
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EPA REVIEW NOTICE
This report has been reviewed by the Environmental Protection Agency
and approved for publication. Approval does not signify that the
contents necessarily reflect the views and policies of the Agency,
nor does mention of trade names or commercial products constitute
endorsement or recommendation for use.
11
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TABLE OF CONTENTS
Section Page
LIST OF FIGURES viii
LIST OF WIRING TABLES xvi
LIST OF DRAWINGS xix
1 INTRODUCTION 1-1
2 SPECIFICATIONS 2-1
System 2-1
Source and Reference Blackbodies 2-1
Telescopes 2-3
Source Modulator 2-3
Reference Chopper 2-k
Monochromator 2-U
Detector 2-U
Detector Cooler 2-5
Preamplifier 2-5
Selective Amplifier 2-6
Lock-In Amplifier 2-6
Source Compensation Amplifier 2-7
Reference Compensation Amplifier 2-7
Source Digital Voltmeter 2-8
Ratic Digital Voltmeter 2-8
Wavenumber Encoder r 2-9
Encoder Control t 2-9
Wavenumbar Display 2-9
Strip Chart Recorder 2-9
Digital Data Coupler 2-10
Digital Printer 2-U
Magnetic Tape Recorder 2-11
111
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TABLE OF CONTENTS
(Continued)
Section
3 SYSTEM DESIGN 3-1
3.1 OVERALL SYSTEM REQUIREMENTS 3-1
3.2 SYSTEM DESCRIPTION 3-5
3.3 RADIOMETRY 3-1?
3.3.1 Signal Equations 3-17
3.3.2 Etendue 3-35
3.3.3 Transmission 3-51
3.3.1* Modulation Factor 3.56
3.3-5 Spectral Slit Width 3_63
3.1* OPTICAL SYSTEM DESIGN 3-70
3.U.I Blackbodies 3-70
3.1*.2 Telescopes 3-72
3.1*.3 Reference Optics 3-79
3.l*.l* Monochromator 3-79
3.1*.5 Detector Optics 3-86
3.U.6 Detector 3-97
3.1*.7 Synch Systems 3-98
3.5 MECHANICAL SYSTEM DESIGN 3-IOC
3.5.1 Stands 3-10C
3.5.2 Telescopes 3-101
3.5.3 Reference Optical System Mounts 3-115
3.5.1* Detector Optical System Mount 3-H7
3.5.5 Detector Cooler 3-H7
3.5.6 Detector ...."...' 3-120
3.5.7 Synch Systems 3-120
3.6 ELECTRONIC SYSTEM DESIGN • • 3-121
3.6.1 The Electronic System 3-121
3.6.2 Signal Sources 3-121
3.6.3 Signal Amplifiers 3-122
3.6.1* Wavenumber Generation 3-125
3.6.5 Data Acquisition Subsystem 3-127
3.6.6 Data Recording Subsystem 3-131
3.6.7 Electronics Calibration 3-135
3.6.8 Power Subsystem 3-135
IV
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TABIE OF CONTENTS
(Continued)
Section
U COMPONENT DETAILS
U.I OPTICAL COMPONENTS .............. U-l
U.I.I Blackbodies ................. U-l
U.I. 2 Telescopes . ................. ^-5
U.I. 3 Reference Optics ............... U-15
U.l.U Monochromator ................ U-17
U.I. 5 Detector Optics ............... U-25
U.I. 6 Detector ................... U-27
U.I. 7 Synch Systems ................ U-3U
U.I. 8 Alignment Systems ......... ..... U-3U
U.2 MECHANICAL COMPONENTS ............ U-36
U.2.1 Stands .................... U-36
U.2. 2 Auxiliary Stands ..... .......... U-U3
U.2. 3 Electronic Consoles ............. U-U5
U.2.U Blackbody Plumbing and Mounting ....... U-U5
U.2. 5 Telescopes .................. U-U9
U.2. 6 Reference Optical System ...... ...... U-U9
U.2. 7 Monochromator .....' ........... U-52
U.2. 8 Detector Optical System ........... U-56
U.2. 9 Detector Mount-Dewar ............. U-58
U.2. 10 Detector Cooler ............... U-58
U.2. 11 Synch Systems ................ U-6l
U.3 ELECTRONIC SYSTEM DETAILS ....... ... U-6?
U.3.1 The Electronic System ............ U-63
U.3. 2 Signal Sources ................ U-63
U.3. 3 Signal Amplifiers .............. U-68
U.3.U Wavenumber Generation ............ U-82
U.3. 5 Data Acquisition Subsystem .......... U-90
U.3. 6 Data Recording Subsystem ........ ... U-101
U.3. 7 Electronics Calibration ........... U-102
U.3. 8 Power Subsystem ............... U-103
v
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TABIE OF CONTENTS
(Continued)
Section Pa6e
5 SYSTEM OPERATION 5-1
5.1 PRELIMINARY CALIBRATIONS 5-1
5.1.1 Blackbody Calibration 5-1
5.1.2 Electronic Calibration 5-1
5.1.3 Monochromator Calibrations 5-3
5.2 SYSTEM INSTALLATION 5-3
5.2.1 Site Selection 5-3
5.2.2 Stand Set Up 5-U
5.3 STARTING THE SYSTEM 5-6
5.3.1 Blackbodies 5-6
5.3.2 Detector Cooler 5-6
5.3.3 Choppers 5-8
5.U TEST PARAMETER SELECTION 5-9
5.U.I Spectral Parameters 5-9
5.U.2 Slit Height 5-10
5.1*.3 Slit Width 5-10
5. U.I* Time Constant-Scan Speed Relation 5-21
5.1*.5 Selective Amplifier Q 5-33
5.5 PROCEDURE 5-37
5.5.1 Monochromator • 5-37
5.5.2 Wavenumber Generation System 5.39
5.5.3 Amplifiers-Emission 5_llO
5.5.1* Amplifier-Transmission 5_ll2
5.5.5 Data Recording Systems 5.1*5
5.5.6 Scanning the Spectrum 5.1*7
5.6 SYSTEM SHUT DOWN 5.1+9
5.6.1 Blackbodies 5-1+9
5.6.2 Detector Cooler 5.50
PERFORMANCE
6-1
6.1 LABORATORY TESTS . . . 6-1
6.1.1 Signal 6-1
6.1.2 Noise 6-3
VI
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TABLE OF CONTENTS
(Continued)
Section
6 PERFORMANCE (Continued)
6.1.3 Typical Scans ........... ..... 6-U
6.2 FIELD TESTS ................. 6-1*
6.2.1 Signal .................... 6-7
6.2.2 Noise .................... 6-7
6.2.3 Typical Scans ................ 6-9
7 MAINTENANCE ...................... 7-1
7.1 OPTICAL MAINTENANCE ............. 7-1
7.1.1 Blackbodies ................. 7-1
7.1.2 Telescopes .................. 7-1
7.1.3 Reference Optics ............... 7-2
7.1.U Monochromator ......... ....... 7-2
7.1.5 Detector Optics ............... 7-3
7.1.6 Detector ............ ....... 7-3
7.1.7 Synch System ............... . . 7-^
7.1.8 Alignment Device ............... 7-U
7.2 MECHANICAL MAINTENANCE ............ 7-k
7.2.1 Stands .................... 7-5
7.2.2 Auxiliary Stands ............... 7-5
7.2.3 Electronic Consoles ............. 7-5
7.2.U Telescopes .................. 7-5
7.2.5 Reference Optical System ........... 7-5
7.2.6 Monochromator ................ 7-5
7.2.7 Detector Optical System ........... 7-6
7.2.8 Detector Cooler . . . . ........... 7-6
7.2.9 Synch Systems ................ 7-6
7.3 ELECTRICAL MAINTENANCE ............ 7-6
7.3.1 Signal Sources ................ 7-6
7.3.2 Signal Amplifiers .............. 7-6
7.3.3 Data Acquisition System ........... 7-6
7.3.U Data Recording System ............ 7-7
7.3.5 Pover Sources ................ 7-7
7.3.6 Fuse List .................. 7-7
8 WIRING TABLES ..................... 8-1
8 DRAWINGS (Reduced Size) . . . ............ . 9-1
vii
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LIST OF FIGURES
Caption
3.2.1 System Block Diagram
3-9
3.2.2 Photo: Source Stand
3-10
3.2.3 Photo: Receiver Stand- Left Side
3.2.U Photo: Receiver Stand - Right Side
3-12
3.2.5 Photo: Electronic Enclosures
3.2.6 Photo: Counter and DVM's 3-13
3.2.7 Photo: Digital Recorders 3-lU
3.2.8 Photo: Data Processor and Control 3-15
3.2.9 Photo: Analog Recorder-Temp. Control 3-l6
3.3.1.1 Emission Mode of Operation Schematic Optical Diagram 3-18
3-3.1.2 Transmission Mode of Operation Schematic Optical 3-2U
Diagram
3.3.1.3 "Decontamination" Schematic 3-30
3.3.2.1 Emission Mode Field of View 3-38
3-3.2.2 Transmission Mode Geometry . 3-39
3.3.2.3 Net Transmitting Area - 9 = 20° 3-M
3.3.2.U Net Transmitting Area - 9 = 30° 3-^2
3.3.2.5 Net Transmitting Area - 9 = 1*0° 3-^3
3.3.2.6 Vignetting Factor 3-M*
viii
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LIST OF FIGURES
(Continued)
Figure Caption Page
3.3.2.7 Total Image Height vs Range 347
3.3.2.8 Grating Angle « ^
3.3.2.9 Average Integrated Vignetting Factor 3.1*9
3.3.2.10 Etendue Ratio 3.50
3.3.3.1 External Specular Transmittance - Irtran 2 (Uncoated) 3-52
3.3.3.2 Aluminum Reflectance 3.53
3.3.3.3 Grating Efficiency 3.55
3.3-U.I Single Chopper Modulation 3.58
3-3.U.2 Dual Chopper Modulation 3-&>
3-3.U.3 Modulation Factor 3_£2
3.3.5.1 Image Intensity Distribution 3-6U
3.3.5.2 Integrated Output Intensity Distribution 3-6U
3.3.5.3 Diffraction Contribution Function 3-66
3-3-5.U Spectral Slit Width 3-68
3.U.I Optical System Schematic 3-71
3.U.1.1 Source Blackbody and Ray Envelope; Range = O.U km 3-73
3.U.I.2 Source Blackbody and Ray Envelope; Range = U.O km 3-7U
3.U.2.1 Telescope Performance 3.76
3.U.2.2 Telescope Length Comparison 3.78
ix
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LIST OF FIGURES
(Continued)
Figure Caption Page
3.^.^.1 Monochromator Optical Diagram 3-8l
3.U.U.2 Double Diffraction Limiting Incident Rays 3-83
3.U.U.3 Double Diffraction Wavelength Ranges
3.U.5.1 Detector Optical Systems 3-8?
3.U.5.2 Dan Kirkham + 90 Degree Ellipse 3-89
3.^.5.3 Telescope System + 90 Degree Ellipse 3-90
3.U.5.U Dall Kirkham + On-Axis Ellipse 3-91
3.1*.5.5 Telescope System + On-Axis Ellipse 3-92
3.U.5.6 Dall Kirkham + Detector "Cassegrain" System 3-91*
3.U.5.7 Telescope System + Detector "Cassegrain" System 3-95
3.U.5.8 Effect of Monochromator on Emission Mode Performance 3-9°
3-99
3.U.7.1 Source Synch Receiver
3-105
3.5.2.1 Temperature Differences in a Slab
3.5.2.2 Telescope Mirror Sections for Thermal Analysis **"
3.5.2.3 Transient Temperature Differences in a Telescope Mirror 3~ 9
3.5.2.U Telescope Mirror Sections for Thermal Analysis •*"
3-113
3.5.2.5 Temperature vs Time of Telescope Elements
3-ii6
3.5.2.6 Difference in Position of Focus & Entrance Slit "^
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LIST OF FIGURES
(Continued)
Figure Caption Page
U.I.1.1 Blackbody Warmup History U-3
U.I.1.2 Blackbody Temperature Profile U-U
U.I.2.1 Telescope Optical Diagram U-6
U.I.2.2 Dall-Kirkham System Performance U-8
U.I.2.3 Telescope System Performance U-9
U.1.2.U Telescope Test Source U-ll
U.I.2.5 Telescope Test Set-Up UJ-3
U.I.3.1 Reference Optics Diagram U-l6
U.I.U.I Filter Transmission U-18
U.1.U.2 Grating Mask UJ-9
U.1.U.3 Slit Height Assembly Schematic U-20
U.l.U.U Gases Useful for Wavenumber Calibration U-23
U.1.U.5 Deviations from Wavenumber Linearity U-2U
U.I.5.1 Detector Optics Diagram U-26
U.I.6.1 Detector Spec. Drawing U-28
U.I.6.2 Detector Off-Axis Response U-33
U.2.1 Source and Receiver Assemblies U-37
U.2.1.1 Stand Assembly U-38
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LIST OF FIGURES
(Continued)
Figure Caption Page
U.2.1.2 Stand Pad Details l+.Ul
U.2.1.3 Stand Wheel Details U-U2
U.2.1.U Stand Connection Panel k-kh
I*. 2.^.1 Blackbody Interconnections U-k6
U.2.U.2 Blackbody Geometry & Plumbing 1|-U8
U.2.5.1 Telescope General Assembly U-50
U.2.7.1 Monochromator Mount Detail U-53
U.2.7.2 Wavenumber Drive Details U-5^
U.2.8.1 Detector Optical System Details U-57
U.2.9-1 Detector Installation U-59
h.2.10.1 Detector Cooler Details U-6o
U.2.11.1 Reference Synch LED and Photodiode l|-62
^.3.2.1 Detector Circuitry U-6U
U.3.2.2 Reference Synch Detector U-65
U.3-2.3 Encoder Interconnections U-66
U.3.2.U Encoder Dimensions ^-67
U.3.3.1 Preamplifier Interconnections U-68
^.3.3-2 Selective Amplifier Signal Connections U-69
xii
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LIST OF FIGURES
(Continued)
Figure Caption
^.3.3.3 Source and Reference Compensation Amp U-71
U.3.3.U Source Synch Preamp ^-^
^.3.3.5 Source Synch Preamplifier Interconnections U-7"
U.3.3.6 120 Hz Gyrator ^-^
U.3.3.7 Interconnection of Gyrator ^-7°
U.3.3.8 Source and Ref Synch Amplifiers ^-79
U.3.3.9 Source Synch Amplifier Interconnections U-80
U.3.3.10 F.eference Synch Amplifier Interconnections U-81
U.3.U.1 Data Control Monostable ^-89
U.3.I|.2 Interconnection of Data Control ^-89
U.3.5.1 Bi-Directional Counter Interconnections U-90
U.3.5.2 Sample Hold DVM 5^03-015 Interconnections U-91
U.3.5.3 Ratio DVM 5U03-010 Interconnections U-92
U.3.5.U I/I Ratio Module **-93
U.3.5.5 I/I Block Diagram ^-9^
U.3.5.6 I/I and Recorder Select Switch Interconnections U-9&
U.3.5.7 Data Coupler Interconnections ^-9°
U.3.5.8 Marker Control 1*-100
xiii
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LIST OF FIGURES
(Continued)
Figure Caption Page
4.3.6.1 Strip Chart Recorder Interconnections 4-101
4.3.7.1 Standard Signal Generator 4-102
U.S.8.1 ^2k V dc Interconnections 4-104
4.3.8.2 *6 Volt Power Supplies 4-105
U.3.8.3 Reference Chopper Motor Drive 4-107
4.3.8.4 Chopper Motor Drive Interconnections 4-108
5.2.2.1 Stand Pad Alignment 5-5
5.3.1 Typical Starting Schedule 5-7
5.U.3.1 Spectral Line Response 5-12
5.4.3.2 dv/dx vs s/a 5-14
5.4.3.3 Exit Slit Irradiance 5-15
5.4.3.4 Diffraction Parameters 5-22
5.4.4.1 RC Filter Response 5-24
5.4.4.2 Time Constant - 0.1 cm Delay . 5-26
5.4.4.3 Time Constant - Peak Error 5-28
5.4.4.4 Time Constant - Scan Speed Logic 5-29
5.4.4.5 Time Per Resolution Element 5-32
xiv
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LIST OF FIGURES
(Continued)
Figure Caption Page
5.1*.5.1 Selective Amplifier Relative Response 5-31*
5.U.5.2 Selective Amplifier Relative Response Near fo 5-35
5.U.5.3 Selective Amplifier Phase Response 5-36
6.1.3.1 Typical Laboratory Scans 6-5
6.1.3.2 The R5 Line of CO 6-6
6.1.3.3 Ozone Spectrum 6-6
6.2.3.1 Typical Field Test Scans 6-10
xv
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LIST OF WIRING TABIES
Card Layout
SI
S3
S5
S7
S9
Sll
S13
S15
SI?
S19
S21
S23
S25
Jl
J2
J101
P101
S2
Sk
S6
S8
S10
S12
SlU
S16
Sl8
S20
S22
S2U
PI
P2
J102
P102
Page
8-1
8-2
8-3
8-1*
8-5
8-6
8-7
8-8
8-9
8-10
8-11
8-12
8-13
8-lU
8-15
8-16
8-17
8-18
xvi
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LIST OF WIRING TABIES
(Continued)
J103
J10U
P10U
P106
J107
J108
J109
P110
Pill
J112
J113
JllU
J115
J116
J117
J118
J119
J120
P103
J105
P105
J106
P107
P108
P109
JUO
Jill
P112
PH3
PllU
P115
Pll6
P117
P118
P119
P120
8-19
8-20
8-21
8-22
8-23
8-2U
8-25
8-26
8-27
8-28
8-29
8-30
8-31
8-32
8-33
8-3^
8-35
8-36
xvii
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LIST OF WIRING TABIES
(Continued)
Page
Control Panel Wiring 8"37
Coaxial Cables 8-38
Recorder Input SW1 Recorder Input SW2 8-39
Data Acquisition System Cables 8-UO
Monochromator Controller 8-Ul
xviii
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LIST OF DRAWINGS
Caption Size
596-722-003
ook
005
006
007
008
009
010
on
012
013
01*t
015
016
017
018
019
General Assembly - Remote Optical Sensing of Emission
System
Mount, Monochromator and Source Blackbody
Support Structure Assembly
Stand Assembly
Optical Components - Reference Optics System
Optical Components - Detector Optics System
Dewar Assembly
Reference Optical System
Detector Optical System
Slit Height Assembly
Modified Wavenumber Drive
Alignment Devices
Encoder Installation
Cryocooler Equipment
Source Synch Receiver
System Nameplate
Auxiliary Stands
D
D(2)
D(5)
D(5)
C
C
C
D(7)
D(3)
D
D
D(2);C
C
C(2)
D
C
D
020 Electronic Consoles
xix
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LIST OF DRAWINGS
(Continued)
Number Caption Size (Shts)
596-722-021 System Block Diagram D
022 Recorder Input Switch C
023 Source Synch Preamp c
02k 120 Hz Gyrator C
025 Standard Signal Generator C
026 Source and Reference Synch Amp C
027 Source and Reference Compensation Amp C
028 ± 6 V Power Supply C
029 Chopper Motor Drive C
030 I/I Ratio Module C
031 Data Control Monostable C
032 Wavenumber Logic Diagram Special
033 Interconnection Diagram D
03^ Grating Masks c
035 Recorder Marker Selector C
036 Elevation Mirror D(3)
xx
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1.0 INTRODUCTION
This report constitutes partial fulfillment of Contract CPA 22-69-1U2 between
the Environmental Protection Agency and General Dynamics/Convair Aerospace
(San Diego) and describes the overall and detail instrument design, as well as
initial acceptance test performance. The work was performed in the
Environmental Sciences Section of the Sensor Technology Group in the Engineer-
ing Department of Convair Aerospace. The program leader was Dr. Claus B.
Ludwig, assisted by Dr. M. Griggs; they were responsible for the spectroscopic
design. M. L. Streiff was responsible for the optical and mechanical design
and construction (he conceived the dual chopper system) and performed final
system checkout. C. R. Claysmith was responsible for the electronic design
and construction. Work started in June 1969 and acceptance tests were per-
formed during 1971. The ROSE system was delivered in early 1972. The
government project officers were Mr. John S. Nader and Dr. William F. Herget.
The instrument may be used to measure transmission of urban atmospheres,
using a remote source (up to k kilometers) or to measure emission from sources
such as smokestacks. It is designed to measure the absorption or emission caused
by pollution by scanning spectrally in the 3 to 5.5 micron and 7 to 13.5 micron
regions. Data may be recorded on a strip chart recorder, a digital printer,
and/or a magnetic tape recorder. Digital and analog displays or wavenumber and
signal output (either source or reference) and the ratio (transmission) of the
source to reference signals are provided. The system is designed to be easily
transported for field use.
Details of field tests with this system are given in a separate report under a
follow-on contract. This latter contract also covers an elevation mirror to
make observation at large vertical angles easier.
In the next section a summary of specifications is given for convenient reference,
A discussion of the system design is given in Section 3.0, followed by a des-
cription of component details in Section U.O. Set-up procedures and operation
are given in Section 5.0. The system performance in the laboratory and the
results of initial field tests are given in Section 6.0 and maintenance
recommendations are given in Section 7.0. Wiring Tables are located in Section
8.0 and reduced size drawings are shown in Section 9«0«
Figure numbers are assigned in sequence within each subsection; e.g., the
third figure in Section 3.U.2 is designated Figure 3.U.2.3. Pages are numbered
within each major section; e.g. the 98th page in Section 3.0 is designated 3-98-
1-1
-------
The authors would like to acknowledge the cooperation of many persons during
the design and construction of the ROSE system, especially the invaluable
discussions with L. L. Acton and G. D. Hall of the Environmental Sciences
Section.
We also wish to acknowledge the assistance of L. J. MacDonald of the Purchasing
Group and C. N. Abeyta, C. Baker, E. R. Bartle, Dr. W. Malkmus, and
L. C. Wilson of the Environmental Sciences Section.
1-2
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2.0 SPECIFICATIONS
The following condensed specifications are a combination of test data and manu-
facturer's data (as indicated by an asterisk). Metric and English units are
given (except weights and sizes are in English units only). For more complete
specification data, refer to the individual component manuals or the Component
details section of this report.
System
Design Range:
Spectral Regions:
Resolution:
Scan Time:
Display:
Recording:
Ambient Temperature:
Relative Humidity:
Portability:
Source Power:
Receiver Power:
(Transmission) O.U to U.O km (0.25 to 2.5 miles)
3 to 5.5 microns (1820 to 3330 cm"1)and
7 to 13.5 microns (7^0 to lU30 cm"1)
to 0.01 microns
2 minutes minimum (either spectral region)
130 minutes maximum (either spectral region)
Wavenumber, I, I/IO
Analog and digital
0 to 38°C (32 to 100°F)
0 to 95$
All units mounted on casters
115V 60 Hz 1 phase 12 amp start; 8 amp run
115V 60Hz 1 phase 32 amp start; 2U amp run
Source and Reference Blackbodies
Mfgr. & Model:
Max. Temperature:
Operating Temperature:
Electro Optical Ind., Santa Barbara, Ca.
Model WS135R cavity; Model 9l6 cooler;
Model 2l6A Temperature control
*1900°K
1800°K
2-1
-------
I
Temperature Stability: ± U C
Emissivity: *0.99 ± 0.01
Aperture: 12.7 x 6.3 mm (0.50 x 0.25in.)
Cooling: Ethylene glycol closed loop with ambient heat
exchanger
Warm-up Time: Approximately 90 minutes(standby)
195 minutes (cold start)
Lifetime: ^-Approximately 700 hours
Aperture Set: *0.0125, 0.025, 0.05, 0.10, 0.20 inch diameter
and wide open (0.5&2 inch)
Internal Temperature Monitor: Included
External Radiation Probe: Included
Power Required: 115V 60 Hz
Start Run
Cooler
Temperature Control
Weight & Size*
Cavity
Cooler
Temp. Controller
2.2 amp
10
Ibs L
25 12"
30 (est) 19"
Uo lU"
2.2 amp
5.8
W H
8" 10.5"
10.5" 11"
19" 7"
2-2
-------
Telescopes
Mfgr. and Model:
Type and f/no:
Focal Length:
Clear Aperture:
Field of View:
Blur Circle Diameter:
Primary f/no:
Perkin Elmer (Costa Mesa, Ca.) Model 700
Dall .Kirkham f/5.0
3C&.8cm (120 inches)
6l.Ocm (2k inches)
0.25 degree (±0.125 degrees)
150 microns
2.0
Secondary Magnification: 2.5
Mounting Plane to Focus: 30.^8cm (12.0 inches)
Overall Tube O.D.: 28 inches
Overall Length:
Weight:
Source Modulator
Mfgr. and Model:
Frequency*:
Operating Freq:
WC Freq. Monitor*
Stability:
Warmup Time:
Power Required:
36 inches
130 pounds
Electro Optical Ind. (Santa Barbara, Ca.) Model 3H
30 - 3000 Hz continuously variable (2^ slot blade;
Freq. = 3.0 x meter rdg)
570 Hz
(PPS = 3-75 x meter rdg)
±0.5$ (* ±0.1$
Approximately 1 hour (to within -0.5$)
115V 60 Hz 0.3 amp
2-3
-------
Reference Chopper
Mfgr:
Frequency:
Stability:
Warmup Time:
Power Required:
Monochromator
Mfgr. and Model:
Type:
Gratings:
Slits:
Wavenumber drive:
Min. scan time:
Scan Control:
Size:
Weight:
Detector
Mfgr. and Model:
Type:
Operating Temp:
Size:
Field of View:
D*(Xm, 630):
R(Xm, 630):
Resistance:
Oonvair
330 Hz
± 0.3 Hz
Approximately 30 minutes
1.2 amp.
Perkin Elmer (Norwalk, Conn.) Model 210B
Littrow grating with linear wavenumber drive
3 - 5.5n; 2hO 1/nm 20° 3^00 cm"1 (2.9^0
7 - 13.5« 101 I/mm 22°2' 1333 cnT^T-Sn)
Masked to 15.9 cm^ net area (nominal)
Width; 0 to 2.0 mm micrometer controlled
Height; 0 to 12.0 mm micrometer controlled
3/32 to 6 rpm in steps of 2 x
Approximately 2 minutes
Perkin Elmer 012-0466
17.5" x 2k" x 12"
64 pounds
Santa Barbara Research Center (Goleta, Ca.) 8679-1
Mercury doped Germanium
26°K (58 psia Ha)
0.2 x 2.0 mm
90°
0.84 x lO1^ Hz 2/watt
12.0 x 10^ volts/watt
12.8K
2-k
-------
Detector Cooler
Mfgr. and Model:
Type:
Cryogenic Technology Inc. (Waltham, Mass.)
Model 20 with 3833-005 temperature controller.
Closed cycle He refrigerator consisting of com-
pressor and cold head connected by flexible hoses,
Operating Temp. Range: Approximately l6 to 28°K
Operating Temperature: 26 K (58 psia Ha)
Temperature Stability: ± 0.1 K (± 1 psia Ha)
Cooldown Time:
Power Required:
Approximately 15 minutes
115V 60 Hz
Compressor
Temp. Control
Start
~ 15 amp
~ 0.1
Run
10 amp
~ 0.1
Size:
Weight:
Preamplifier *
Mfgr. and Model:
Type:
Compressor 20"L x 13"W x 13"H
Cold Head 8"L x V'W x 12"H
Temp. Controller 11"L x 12"W x 7"H
Compressor 70 pounds
Cold Head 11 poionds
Princeton Appl. Research Corp. (Princeton, N.J.)
Model 213
RC coupled, single ended low-noise
Direct Input Impedance: 10 megohms shunted by less than 20 pf
(transformer input also available)
Frequency Response
Gain:
± 0.2 db from 10 Hz to 100 Khz
Switch selectable from 1 to 1000 in 1, 2, 5
sequence plus vernier (± 1$ at f = 1 Khz)
2-5
-------
Noise:
Max output:
Output Impedance:
Power Requirement:
Size:
Weight:
Selective Amplifier *
Mfgr and Model:
Input Impedance:
Frequency Range:
Frequency Stability:
Gl Range:
Gain:
Max Output:
Output Impedance:
Power Requirement:
Size:
Weight:
Lock-In Amplifier *
Mfgr and Model:
Input Impedance:
At 300 to 600 Hz and 5>600 ohms source re-
sistance (12.8K in parallel with 10K) the
noise figure is about U db
20V peak to peak @ 100 Khz
600 ohms
± 2UV @ 38 ma (from NIMBIN)
8.8"H x 2.7"W x 10"L
3 Ibs
Princeton Appl. Research Corp. (Princeton
N.J.) Model 210
1 megohm shunted by less than 20 pf (thru
0.5 uF)
1 Hz to no KHz
0.02j6/°C typical; 0.02$/2U hr at constant
temp.
1 to 100 in 1, 2, 5 sequence
1 or 10
5 volts RMS
600 ohms
± 2UV @ 100 ma (from NIMBIN)
8.8"H x 2.7'V x 10"L
U Ibs.
Princeton Appl. Research Corp. (Princeton,
N.J.) Model 220A
1 megohm shunted by 30 pf
2-6
-------
Frequency Range: 1 Hz to 110 KHz
Sensitivity: 0.1, 0.2, 0.5 or 1.0 volts rma input for
full scale ± 10V DC output (referred to
as gains of 100, 50, 20 or 10 respectively)
Time Constant: 0.03 ms to 1 second in 1, 3, 10 sequence
6 db per octave roll-off
Linearity*: Better than 0.1$ of full scale
Max Output: ± 10V DC
Output Impedance: Direct Mixer = 100 ohms Monitor » 5,000 ohms
Synch Input Impedance: 10K ohms
Synch Modes: Sel Ext (used for normal operation), Ext.,
Int., Int 2F and Cal 10 mv.
Synch Output Impedance (Cal Output): 50 ohms
Calibration Output: 18 mv pp square wave (8.1 mv rms fundamental)
Source Compensation Amplifier
Mfgr and Model: Convair; no model number
Type: Non-inverting operational amplifier
Input Impedance: ~ UOO megohms
Gain: 8.0
Output Impedance: < 1 ohm
Reference Compensation Amplifier
Mfgr and Model: Convair; no model number
Type: Differential operational amplifier
Source signal; + input
Reference signal; - input
Input Impedance: ~ UOO megohms
Gain: 1.00
Output Impedance: < 1 ohm
2-7
-------
Source Digital Voltmeter *
Mfgr and Model: Dana Labs Inc. (Irvine, Calif.) Model 5^03
with Model 015 plug-in sample and hold; 66-D2
isolated output option
Input Impedance: 10V range, 1000 megohms; other ranges 10 megohms
Accuracy:
Temp. Coeff:
Display:
Maximum Display:
± 0.01$ of reading ± 0.01$ of full scale
0.001$ of fuOl scale/'C
Five digits plus decimal point
10.999 volts
May be programmed to read on manual or
external system command
Power Requirements: 115V 60 Hz O.U amp
Size: 19"W x 17"L x 5"H
Weight: 25 Ibs.
Ratio Digital Voltmeter *
Mfgr and Model: Dana Labs. Inc. (Irvine, Calif.) Model 5^03
with Model 010 plug in (DC and ratio; 66-D2
isolated output option
10V range, 1000 megohms; other ranges 10 megohms
±0.01$ of reading ± 0.01$ of full scale
0.001$ of full scale/°C
Five digits plus decimal point (10 x ratio)
10.999 (ratio = 1.0999)
May be programmed to read automatically or
on external system command
Power Requirement: 115V 60 Hz O.U amp
Size: 19W x 1?"L x 5"H
Weight: 25 Ibs
Input Impedance
Accuracy:
Temp. Coeff:
Display:
Maximum Display:
2-8
-------
Wavenumber Encoder
Mfgr and Model: Dynamics Research Corp. (Stoneham, Mass.)
Model 35-1-001-9000
Counts per Revolution: 9000
Power Requirements: + 6V @ 0.31 amp; - 6V @ O.OU amp
Encoder Control
Mfgr and Model:
•type:
Slope Range:
Wavenumber Display
Mfgr and Model:
Input Impedance:
Display:
Maximum Display:
Power Requirement:
Size:
Weight:
Strip Chart Recorder *
Mfgr and Model:
Input Impedance:
Convair; no model number
Bidirectional logic with variable slope
3-5.5 micron; 112.5 to lUU.5cm /turn
7 - 13.5 micron; 50.0 to 56.8cm /turn
(Slope dial in units of O.lcm /wavenumber
drum turn)
Anadex Instr. (Van Nuys, Calif.)
Model CB600R (options BZ, BL, G-UA, A)
1 megohm in parallel with 80 pf
5 digits
99999 (9999.9cm1)
Preset switch for setting wavenumber for
zero on wavenumber drum.
115V 60 Hz 0.3 amp
19"W x 12"L x 3.5"H
15 Ibs
Hewlett Packard (Palo Alto, Calif.)
Model 7701B with Model 8801A plug in
(heated stylus)
Balanced to gnd; 500K ohm ± 1^ in parallel
with 100 pf each side
2-9
-------
Strip Chart Recorder (continued)
Input Ranges: 5 mv to 5 volts/div inl, 2, 5 sequence
Frequency Response: DC to 30 Hz
0.25 dlv.
0.035"j6/*C; 0.06jt/£ line voltage
0.5, 2.5, 10 or 50 mm/sec or ram/min.
10m wide (50 div full scale)
time lines every 5 mm
Perma paper 651-217 (200 ft)
Included
115V 60 Hz 0.6 amp
19'V x 17.5"L x iV'H (in rack mtg adapter)
20 Ibs
Linearity:
Gain Stability:
Chart Speeds:
Chart:
Event Marker-:
Power Requirement:
Size:
Weight:
Digital Data Coupler *
Mfgr and Model:
Type:
Zehntel Inc., Berkley, Calif. Model 61*9
Custom built to accept data from digital
voltmeters and counters and transfer the
data to the tape recorder and/or the
digital printer with proper data format
conversion.
Modes and Cycle Time: Record Only; 26 ms + reading time
Print Only; 50 ms + reading time
Record and Print; 50 ms + reading time
Reading time approx. 2 to 3 ms normally
without range change.)
Power Requirement: 115V 60 Hz 0.3 amp
2-10
-------
Digital Printer *
Mfgr and Model:
Data Input:
Printing Rate:
Column Capacity:
Output Format:
Paper:
Power Requirement:
Magnetic Tape Recorder *
Mfgr and Model:
Date Input:
Recording Rate:
Tape Format:
Tape Used:
Power Requirement:
Size:
Weight:
Hewlett Packard (Palo Alto, Calif.)
Model 5050B
Parallel entry BCD;"!" state positive
20 lines/second
18 columns
I, 1* columns; I/I ,^ columns; Wavenumber,
5 columns
Pressure sensitive (9281-038?; 15,000
lines/pack)
115V 60 Hz 0.8 amp
Kennedy Co. (Altedena, calif.) Model 1600/H5
500 characters per second
7 track NRZI (6 data cha. plus parity)
0.5" wide 1.5 mil computer tape (up to 8.5"
dia reels IBM compatible)
115V 60 Hz 0.8 amp
19" W x 10"L x 12.2"H
UO Ibs
2-11
-------
3.0 SYSTEM DESIGN
After setting forth the system requirements in Section 3.1 in terms of the
contract,a brief description of the system is given in Section 3.2. System
radiometry is set forth in Section 3.3, in which equations for the signal
for both the emission and transmission modes of operation and an evaluation
of the required parameters are given. The system design per se is divided
into three sections: 3.U Optical System Design, 3.5 Mechanical System Design,
and 3.6 Electronic System Design. Emphasis is given in these sections to
operational characteristics particularly as they are related to the system.
Component details are given later in Section U.O.
3.1 OVERALL SYSTEM REQUIREMENTS
The overall system requirements are defined by the Contract (CPA 22-69-1U2)
from which the following scope of work is taken.
3-1
-------
COM1»1CT MO.
SPECIAL PROVISIONS
rPA 2?-M-14? ' —"- -— PAC"
Article 1. Scope of Work
The Contractor, as an independent organization and not as an agent of
the Government, using his best efforts within the time and funds allotted,
shall furnish the necessary labor, material and facilities (unless other-'
wise specified herein) to perform the following work and services:
A. Statement of Work
The contractor shall design, develop, construct, calibrate,
performance check-out, and deliver a field-type research IR
scanning spectropfiotometer with compatible light- source for
long-path operation. The design and performance requirements
include: capability for remote sensing and recording of
eaission^spectra^f hot pollutant gases (ranging in temperature
from 300 to 600° F. and in concentration fron 250 to 3500
parts per million) from stack sources over optical path lengths
up to 300 meters with a viewing angle not to exceed 0.5 degrees-
capability for sensing and recording absorption spectra for
pollutant gases (in concentrations ranging from 0.01 to 1.0
part per million) in urban atmospheres over singel-pass
optical path lengths ranging fron 0.4 to 3 kilometers;
spectral resolution capability of at least 1.0 cnr1 wave
number at iOOO cm"1 and of at least 4 cnr* cm wave number at
2000 cin"1; wavelength scanning for at least the wavelength bands
from about 3.0 to 5.0 microns and from 7.0 to 14.0 microns;
spectral response displayed in terms of a linear frequency*scale;
scan rate tine adjustable down to at least 2 minutes for any one'
band and a capability to cover the entire wavelength band of oper-
ation from 3.0 to 14.0 microns within a minimum time compatible
with the specified resolution; ruggedness for field operation with
portability and system stability to allow for mobile activity in
relocation and transportation and accompanying shock and
vibrations; caintenance of optical alignment, electric stability,
and system calibration under conditions of field operation; a
signal-to-noise ratio, at minimum concentration temperature radiance,
of 2:1 for both the absorption and emission nodes of operation;
and display of output data both in analog forms on a recorder and
in digital print-out.
The following additions criteria shall be met:
(1) Physical dimensions:
a. to permit transport indoors, outdoors, and onto rooftop
by 2 aen
b. to include mirrors < 24 inches in diameter
SPECIAL PROVISIONS FOR NEGOTIATED CONTRACT MEW-U.
3-2
-------
SPECIAL
PROVISIONS
PACE A
•^••^•M
OF 9
^^ ^^»M^«M
J*AGES
(2) Delta S/N optimized for gas with absorption of 50% in 2
kilometer path, line width (half-power, full width, infinite
resolution) of 0.1 cr.pl and Lorcntz shape. Delta S/N
should he equal to or greater than 10 through both bands.
(3) Resolution of 0-Olp in still .atmosphere,
(4) Image dancing fluctuations in a 2 mile path of no more than
50?i should occur v:hen the light beam is deflected by 190
arc-seconds.,
(5) If cooling is necessary for source, it should be a closed
system.
(6) No handling of fluids or gases should be required for the
detectors selected.
(7) Strip chart recorder should be compatible with fast scan
speed of spectrometer.
(8) Digital printout should be capable of speed of-5 linos/sec.
and of handling three parameters, i.e., wavenumber (S digit:;),
I and lo (5 digits each).
(9) Magnetic tape recording shall be provided with selection of
4 sampling rates: 0.1, 0.2, 0.5 and 1.0 err1 or 0.1, 0.2,
0.4 and O.C en
[10) Measure of lo at source shou)d be provided and this information
transmitted for recording at detector location by direct
telephone link or other acceptable means for reference znt
calibration purposes.
B. Hep01ts
1. Nlont^hJy_ Pr oprc ss_ Rgp_or t s
During the period of performance'of this contract the Contractor
r.hall submit five copies of mon-;])ly progress reports to the
Project Officer and one (1) copy to the Contracting Officer.
The report shall bo submitted within fifteen days of the month
succeeding the month covered. This report shall be of brief
narrative type and shall include the following:
a. A brief stp.teir.cnt of work accomplished prior to the stivt
of the current reporting period.
1). A brief statement of work performed during the rcportivig
period, regardlesr of results, including photographs or
charts necessary.
(0-G61
SPECIAL PROVISIONS T01 HECOTIAlEf) COMPACT
3-3
-------
1 I-W1MAC » HO
SPECIAL PROVlStOHS
Or
I'AC.CS
c. Any technical problems, schedules changes, etc., that will
assist the Project Officer in evaluating the Contractor's
progress.
d. A statement of work to be accomplished in the next reporting
period.
e. Status of fund? expended for the month and cumulative and
including a graph comparing projected and actual cor.ts.
2. Final Reports
a. The Contractor shall submit to the Project Officer for
review, three draft copies of the final report within
fifteen calendar days after the completion of the work
called for under this contract. The report shall document
in detail all of the work performed under the contract
including data, analyses, and interpretations as well as
recommendations and conclusions based upon the results
obtained. The report shall include tables, diagrams,
curves, photos, and drawings in sufficient detail to
comprehensively explain the results obtained.
b. The Government shall review r.nd return the draft copy
witli any consents within fifteen days of receipt of the
draft.
c. Iv'ithin thirty calendar days after receipt G'L the approved
draft copy of the final report, the Contractor sha.U submit
to the Project Officer fifteen copies including a rcpro.lucibl'
master of the final report. One copy shall be furnished to
the Contracting Officer.
d. The Contj.aci.ci sii^ll provide. :.v. instruction !:!?r.'ia.! in
five copies upon delivery of the equipment.
srr.ciAi.
rot: N'.'.
-------
3.2 SYSTEM DESCRIPTION
The system can best be described by reference to the block diagram, Figure 3.2.1.
Each enclosure is indicated by the dashed lines around the components within that
enclosure. Optical paths are indicated by dotted lines.
The system can be used in the transmission or emission mode. In the trans-
mission mode the Source Stand and Source Auxiliary Stand are remotely located
(O.U to U.O km design range) from the rest of the equipment. In the emission
mode these two units are not used.
Consider first the optical path indicated on the block diagram. The remote
source used for the transmission mode consists of a telescope with a blackbody
mounted at its focus. The source modulator (or chopper)is located between the
blackbody and the telescope. These components are mounted on a stand which is
adjustable in elevation and azimuth. Accessories for cooling the blackbody,
controlling the modulator frequency and blackbody temperature are located in the
Source Auxiliary Stand.
The nearly collimated beam from the source is directed toward the receiver
telescope which brings the beam to a focus at the monochromator entrance slit
after passing through the reference chopper. Because of the spread of the beam
from the source, the Source Synch Receiver also intercepts a. part of the beam
which is used to provide the synch signal for the source channel of the electronics,
The receiver chopper is inclined about U5 degrees to the beam and the sides
of the chopper teeth nearest the monochromator are polished and aluminized so as
to reflect the reference beam onto the monochromator entrance slit. The reference
beam starts at the reference blackbody (nominally identical to that used for the
source) which is located in the receiver stand. The reference optical system
transmits the reference beam via the reference chopper to the monochromator en-
trance slit so that the source and reference beams alternately enter the mono-
chromator.
The dispersive system component is a grating monochromator which has two
interchangeable gratings, one for each wavelength region. There is a long pass
filter associated with each grating. The monochromator slit width and height are
both adjustable to accommodate the wide range of image sizes of the system.
Scanning of each grating (dv/dt positive) is provided for with speeds ranging
from 3/32 to 6 RPM of the wavenumber drum. An encoder and logic system convert
rotation of the wavenumber drum into wavenumber units.
3-5
-------
SYSTEM BLOCK DIAGRAM
Figure 3.2.1
14170 596-7&-02f
-------
After passing through the monochromator the "beam goes to the detector via
the detector optical system which forms a reduced image of the monochromator exit
slit on the detector.
The receiver telescope, reference optical system, monochromator, detector
optics and detector are mounted on a stand similar to that used at the source.
This stand is also adjustable for elevation and azimuth.
The electrical signal from the detector has frequency components at the
reference and source chopping frequencies as well as dc and sum and difference
frequencies. These latter components are rejected by the selective amplifiers
and the components at the source and reference frequencies pass to the lock-in
amplifiers.
The source synch signal is obtained from the detector in the source synch
receiver via a preamplifier. The reference synch signal is obtained from a
photodiode which is actuated by reference chopper modulation of the beam from
a light emitting diode.
Since the source beam is chopped by both choppers there is a source dependent
component at the reference chopper frequency which must be eliminated. This is
accomplished by blocking the reference beam in an initial balancing procedure and
adjusting the gain of the reference channel so that the output of the reference
compensation amplifier is zero. Upon removal of the block of the reference
channel the output of the reference compensation amplifier is dependent only on
the reference beam.
The output of the source compensation amplifier is called the I signal and
the output of the reference compensation amplifier is called the Io signal. Pro-
vision is made for adjusting the ratio I/IO by means of the Signal T Adjust
potentiometer.
The I and I/IQ signals are digitized and displayed by digital voltmeters.
The wavenumber is displayed by a bidirectional counter. Each of these three
digital signals are fed to a digital recording system which permits paper tape
printout and/or magnetic tape records to be made.
A strip chart recorder is also provided by means of which 1,1 or I/I
can be recorded in analog form.
3-7
-------
In the emission mode the reference blackbody is run at reduced tempera-
ture (ambient temperature in most cases) and only the reference channel
is used.
A photograph of the source stand assembly is shown on Figure 3.2.2. The
blackbody is located at the focus of the source telescope.
Photographs of the receiver stand assembly are shown on Figures 3-2.3 and
3.2.U. The monochromator entrance slits are mounted at the receiver
telescope focus. The detector optics housing attached to the monochromator
supports the dewar in which the detector is located. The detector cooler
is mounted on top of the dewar and has a cold finger which extends down
through the dewar. The detector is mounted on the bottom end of this cold
finger.
A photograph of the electronic enclosures is shown on Figure 3-2.5. For
identification of the electronic components refer to drawing no. 596-722-020,
and Figures 3.2.6 through 3.2.9.
3-8
-------
Figure 3.2.2 Photo: Source Stand
3-9
-------
Figure 3.2.3 Photo: Receiver Stand - Left Side
3-10
-------
•«*-,.'
Figure 3.2.U Photo: Receiver Stand - Right Side
3-11
-------
Figure 3.2.5 Photo: Electronic Consoles
3-12
-------
Figure 3.2.6 Photo: Counter and DVM's
3-13
-------
>
4
START
FUNCTION
PRINT 4 RECORD J^^L
PRINT ONLT • * • RECORD ONLY ^^^9
f~\ I*
X^/ V^^f STANDBY
pq —
E9 ZEMNTEL
DATA COUPLER CONfNOL MOOt L £49
WRITE ERROR
¥
TAPE WOT READY POWER • H
A
^ w
Off • *ON
Q
"'
Figure 3.2.7 Photo: Digital Recorders
-------
PAR 200
NIM BIN
1 COUN™ x OUTPUT COUHTM y OUTPUT
o
otNE»« 6vmJMc
SIGNAL CONTROL
OET OUTPUT
ENCODER CONTROL
FINE SELECTOR
ONE! TENS
90"0" 110
MODE SELECTOR
LOCK H SOURCE COUP LOCK IN KF
Figure 3.2.8 Photo: Data Processor and Control
3-15
-------
Figure 3.2.9 Photo: Analog Recorder - Temp. Control
3-16
-------
3.3 RADIOMETRY
3.3.1 Signal Equations
This system design section on radiometry is concerned with identifying
and estimating the values of parameters which affect the signal levels. In
either the transmission or emission modes of operation the reference chopper in
front of the monochromator alternately samples the beam from the receiver tele-
scope and the beam from the reference optical system. - For convenience these
beams are called the source beam and the reference beam respectively. The source
beam in the transmission mode of operation is modulated at the source blackbody
in order to allow the electronics to separate the source and reference signals
so that their ratio may be obtained. In the emission mode of operation the signal
output results from the difference between the source and reference beams.
In each beam the flux is controlled by many parameters which includes the
radiance of the source of energy, the geometrical optical properties or etendue,
the transmission of windows, mirrors, etc., the spectral bandwidth and the appro-
priate modulation factors. Those portions of each beam upstream of the reference
chopper are separate and those portions downstream of the reference chopper are
common to both beams. Insofar as possible controlling parameters are placed in
that portion of the system in which the beams have a common path and those para-
meters which cannot be located in the common path are made as nearly identical as
possible.
Emission Mode of Operation
In the emission mode of operation there will be a net effective radiance Ns (X )
at the system entrance pupil. This radiance is a complex function of background
radiance, radiance of the object of interest, radiance of the gas between the
object and the telescope, size and range of the object and spectral properties
of the gases (and particulate matter, if present). The evaluation of this
radiance is treated in detail in the field test report. For instrumental purposes
it is sufficient to write the expression for the signal in terms of this
effective source radiance.
The effective source radiance is actually an average taken over the spectral
slit width of the system, AX,
X + AX
Ng(X ) AX = JV(X )dX
3-17
-------
Toroid
Entrance
Slit
Reference
Chopper
Reference
Blackbody
Figure 3-3.1.1 Emission Mode of Operation Schematic Optical Diagram
3-18
-------
The effective source radiance,after two mirror reflections,passes through
the reference chopper towards the monochromator entrance slit. The reference
blackbody radiance after four mirror reflections (including the chopper) also
passes to the entrance slit with 180° phase shift relative to the source beam
(see Figure 3.3.1.1).
The amplitude of the power variation at the detector may be written:
T Afi AX
c c
N (X)(p)2/2 + N (X)(p)V cos(u) t) + ..,
S S c. d.
N°(X,T )(p) /2 + N°(X,Tr)(p)
TT)
2 2
T An AXlN (X)(p) /2 + N (X)(p) Hn cos(u) t) + .
eels s 2 c.
If ^
N°(X,T )(p) /2 - N°(X,T )(p) M0 cos(u) t)
r r r r t
-------
T = common path system transmission
c
2
AO = common path etendue - cm steradian
c
AX = system spectral "bandwidth - microns
2
N (X) = effective source radiance watts/on steradian micron
s
2
N°(X T ) = reference blackbody radiance watts/cm steradian micron
r r
p = aluminum reflectance - one surface
(u = reference chopper angular frequence - rad/sec
t = time-sec
Notice that there are essentially two terms: one at the reference chopper
fundamental frequency and the other a d.c. term which is not sensed by the
electronics since it is a.c. coupled. Signal components at other frequencies
are not sensed by the electronics because of the tuned selective amplifier;
the factor Mg is the ratio of the pp amplitude/2 at the fundamental frequency to
the peak to peak amplitude of the total power, i.e., the fundamental Fourier
coefficient.
The flow of power is written relative to a cold black detector having negligible
emission.
The peak to peak power of the fundamental component at the detector is:
Pd (PP) = 2TcAncA\ [NS(X,TS)(P)2 -
and the RMS power of the fundamental component at the detector is
Pd (RMS) = Pd (PP) (
The RMS voltage of the fundamental component at the detector is
Sd (RMS) = Rd Pd (RMS)
= Rd ^ Tc ArtcA* [Ns(X,Ts)(p)2 - Nr° (X,Tr)(p)^ ] M2
where R^ = detector responsivity - RMS volts/RMS watt
3-20
-------
In this formulation the spectral variations of responsivity and system
transmission are neglected because these are small over the system spectral
bandwidth.
2 U
The factors (p) and (p) account for the different number of surfaces in
each beam. Alternatively, (p) could be factored out and included with T ;
o G
the remaining (p) in the reference term could be either evaluated or combined
with Nr(X,Tr) to define a radiance at a slightly lower temperature, Tr :
N°
The signal at the detector is amplified by the preamplifier, selectively
filtered by the selective amplifier and synchronously rectified by the lock-in
amplifier.
The reference channel lock-in amplifier output for the emission mode of
operation is,
S = Sd(RMS) G G^ G cos(0 - 0 )
xr ^ p fr xr ^d *synch'
where
fr
preamplifier gain - volts/volt
reference channel selective amplifier gain - volts/volt
reference channel lock- in amplifier gain - d.c. volts/
RMS volt
0
synch
= phase angle of detector signal
= phase angle of synch signal
It is assumed that the phase control of the reference channel lock-in
amplifier is adjusted so that cos(0 - 0 ) = 1.00.
rd 'synch
3-21
-------
S = Sd (RMS) G G, G
XT a p f r xr
= Sd (RMS) G
where G = total gain - d.c. volts/rms volt
S = R T AO AX
xr dec
G G^ G
p fr xr
For the emission mode of operation, the reference lock-in amplifier
is connected to the source compensation amplifier. The output of the source
compensation amplifier is
S = S (8.00)r
cs xr sig
In the emission mode of operation, T . is set equal to 125 (1000 full scale)
so that
sig
S = S .
cs xr
3-22
-------
Transmission Mode of Operation
In the transmission mode of operation the signals must be separated electron-
ically because the reference chopper chops both the reference and source beams.
Referring to Figure 3.3.1.2 the source radiance is composed of alternate flux
levels represented by the source blackbody radiance N^(X,TS) and the source
modulator wheel radiance N&(X,TW) assumed to be black. As before, the value of
NS(X) is the integrated value over the spectral slit width. Before passing through
the atmosphere Ns(\) may be expressed as follows:
?r
N (X) = p N°(X,T )/2 + N°(X,T )M,
s I s s s s •••
No(X,Tw)/2 + No^XjTjMjL cos^ t + n) + ...
2
p N°(X,T )/2 4- N°(X,T )Mi cos^t) + ...
1 s s s s -1-
N°(X,Tw)/2 - N^(
= p
(N°S(X,TS) -
where M = source modulator modulation factor
(peak to peak fund./2)/peak to peak wave
Signal components at multiples of the fundamental frequency are neglected;
they will be discussed later.
For now it is sufficient to note that the d.c. term must be retained (as
well as the cos(ioit) term) since it is subsequently chopped by the reference
chopper.
3-23
-------
N (X) (1-a)
o
Toroid
N (X,T ) (or=e)
g g
Entrance
Slit
Reference
Chopper
Reference
Blackbody
Figure 3.3.1.2 Transmission Mode of Operation Schematic Optical Diagram
-------
The reference chopper combines the source and reference beams by alternately
passing each one. The detector signal may be written as before except that, in
this case, the source radiance has a time dependent term and is dependent on the
transmission mode source beam etendue,
Let A =
and B =
Ng(X) = (p)2 A + B cosC^t) + ... 1
The source radiance is assumed to pass through an absorbing region having
absorptivity, cy, and temperature, Tg. The absorptivity of the reference path
is neglected here since it is assumed that the transmission path is much longer
than the reference path.
The source radiance after passing through the atmosphere and receiver
telescope may be written as follows:
Nsa(X) = Ns (XXl-a)p2 + Ng°(X,Tg)(
-------
^ = T AO M,
d c c
[(A
((A
N°(X,TMp)2 N°(X,Tr)(p)
N°(X,Tg)
-------
The following trignometric identities are used in the subsequent analysis,
cos x cosy = cos(x - y) - sin. x sin y
= cos(x + y) + sia x sin y
= cos(x - y) - sin x sin y
2 cos x cos y = cos(x + y) + cos( x - y)
cos x cos y = \ cos(x + y) + ^ cos(x - y)
Applying this result to the equation for P ,
P = T Afi AX •
d c c
B(l-a)(p) (AQ /AD
U
cos(m + u) )t
B(l-a)(p) (An /An )
o c
cos(
m
cos(tut)
2 °
" |A(l-g)(p) (Ant/Anc) + lP(X,Tg)g(p) - Nf(X,T3
1.0
,T )a(p)
&
M
+ o.
Because the selective amplifiers freely transmit only the tuned frequencies
corresponding to u^ and ujg* only the third and fourth terms are of interest
here. The terms involving (u^ + u^) and (UQ. - ug) are rejected by the selec-
tive amplifiers if these frequencies are far from the tuned frequencies and a.c.
coupling blocks the d.c. term.
3-27
-------
The peak to peak power of the fundamental components at the detector are as
follows:
For the source (at tui):
Pd (PP) = 2 TcAnc
AX
with Pd (RMS) = Pd(pp) 2/2
S (RMS) = Rd pc
d
= RdTcAncAX
2/2
For the reference (at
Sd(RMS) = RaTcAflcA
A(l-or)(p) (Afit/
/2
Anc) M2
[Ng°(X,Tg)a(p
)2 - Nr (
/2
X,Tr)p*jM2
If the uh and u^ signal components of Sd are passed through their respective
selective amplifiers and each synchronously rectified by their respective in-
phase synch signals the signals at the two lock-in amplifier outputs will be:
For the source at (mi):
S = Sd(RMS)Gp Gfs Gxs
xs
= R T An AX
d c c
For the reference at(u>2)
S = Sd(RMS)Gp
XT
= R,T An AX
dec
a/2
N°(X,T
s S
W W
(An /An )M
v v- C
2/2
/2
The source channel lock-in output, Sxs, is not a function of the reference
radiance; the dominant radiance is the source radiance. The reference channel
lock-in output, however, is "contaminated" by being a function of both the
source and reference radiances.
3-28
-------
The following procedure is used to "decontaminate" the reference signal.
With the reference beam blocked by a black surface at temperature, Tb, the
lock-in outputs are summed in the(differential) reference compensation amplifier
which has a gain of ±1.00. The source signal goes to the non-inverting input
and the reference signal goes to the inverting input. The output of the ref-
erence compensation amplifier is in this case
cr
S - S
XS XT
R T Afl AX.
dec
N°(X,T
S S
|N°(X,T ) - N°(X,T )|
1 s s w' w j
(Ant/Anc
. a/2
W w
(An /An )M
_____ u _ j^__^_
2/2
K(X,Tg).(p)2-^(X?Tb)(p)2|M
' /2
= 0
Gfs
This signal is set equal to zero by small adjustment of the reference lock-in
gain, G , which is relatively independent of a or (Ant/Anc).
XJ?
With the reference beam block removed,the reference compensation amplifier
output is identical to that for SCr except Nr(X,Tb)(p)2 is replaced by Nr(X,Tr)(p)
Nfost of the terms are eliminated by the zero condition for S^ leaving:
cr
R T An AX
d c c
- Nr(X,T)(p)
The reference channel signal is now independent of the source radiance.
Figure 3.3.1.3 shows the relations for S1 and S which illustrate the method
of"decontaminating" the reference signal.
3-29
-------
Fre«q> Sel. Anp. Lock-In
S' - 0
cr
N>V * »>y ^>> Ur Vr
If p • 1.0
Q
x«~ 2/2
8 ~
xr
8 ^.
c»
(X,T jffi
7T
If T
AO
S .8 -S
cr xs xr
• ie An
C ~ 0
• r
T . S /S ~
Ind. c§' cr
Figure 3.3.1.3 "Decontamination" Schematic
3-30
-------
This fact may be verified experimentally by blocking the source beam ahead
of the reference chopper and noting the negligible change in the reference
compensation amplifier output.
The output of the source compensation amplifier depends on its gain (= 8.00)
and the T *„ potentiometer setting and equals
sig
cs
S (8.00)r .
xs sig
R T An AX
d c c
[N°(X,T ) - tf>(X,T )] (l-a)(p) (An/An )NL
1 s s w w J t c 1
2/2
^ G (8.00)T .
fs xs sig
The indicated transmission, T. , > is the ratio,
ind.
ind.
cs
cr
[N°(X,T ) - N°(X,T ) (i-a)(An./An
[ s s w w j t <
G^ G G U.00 T .
P fs xs sig
P fr xr
N°(X,TS) = N£(X,Tr) if Ts = Tr and the source chopper blade temperature, TW,
is assumed to equal that of the reference block, Tb. The source chopper blade
is polished on the side nearest the source to reduce chopper blade heating and
is blackened on the side facing the telescope. The manufacturer estimates
that the chopper blade is heated to less than 2 or 3°C above ambient. The tem-
perature of the reference block should also be near ambient. Since the second
terra in the square bracket of both the numerator and denominator of the above
equation are small compared to the first term (about 2% or less) small differences
of the second term and the factor (1/p) may be neglected.
The equation for the indicated transmission then becomes,
3-31
-------
ind.
xs
« G_ G
2 fr xr
(1-a)
where (1-a) represents the true transmission.
The coefficient within brackets is constant for a given set-up and is
adjustable by means of the Tsig.control. Without knowledge of the terms
within the bracket one may select a spectral region where a is known or
negligible and set Tsig.so that Tind> on the ratio D.V.M. equals (1-a) =
or 1.00 respectively.
It is of interest to consider the range ofr
order for T to equal (1-a). As shown in the ne
vary from 1.8 in the laboratory to about 0.25 at a
and S/h ~0.56 (i.e. s ~700 microns). The factor
0.63/0.58 = 1.08. The gains Gfg and GXS should be
GXJ., respectively. Therefore, if Tind is to equal
about 0.25 with negligible vignetting (e.g. in the
at a range of 3 km with the given conditions.
setting required in
t section (AS1/AS2 ) can
range of 3 km with h/h =1.0
Mj/Mg) is approximately
nearly equal to G^ and
(1-a), Tsig must range from
laboratory) to about 1.00
The effect of harmonics and sum and difference frequencies has been neglected
up to this point.
For complex waveforms there will be, in addition to the signals u^ = 2 TT fj.
and u>2 = 2 TT f2 used in the analysis, harmonics nfj, and nf2 which can interact
to produce sum and difference frequencies nfi~f2, nfl+f2> nf2-fij and nfg+f}..
Consider the following table which shows the various frequencies in the
neighborhood of the tuned frequencies fj_=570 Hz and f 2=330 Hz.
n
nf2-fl
1 570 Hz
2 llUO
3 1710
2hO Hz
810
1380
900 Hz
2040
330 Hz
660
990
-2kO Hz
90
teo
900 Hz
1230
1560
3-32
-------
Assuming equal radiances in both beams and no absorption or vignetting and
square wave modulation, the relative rms signal strengths at the detector for the
various harmonics are as follows (normalized to a unit reference frequency
signal).
n
0(D.C.)
1 1.00 0.6k
2 0.33 0.21
3 0.20 0.13
0.6k
0.21
0.13
(2.36)
1.00
0.33
0.20
0.21
•
0.13
0.21
0.13
The closest harmonic signal frequency component to f2=330Hz is at (nf-^fg) = 2^0 Hz
and Af/f equals 90/330 = 0.2?. (The fifth harmonic of the line frequency is 300 Hz
which gives Af/f = 30/330 = 0.091; the amplitude of this harmonic is much smaller
than its fundamental, however). The closest harmonic signal frequency component
to fi = 570 Hz is at (nf2-fi) = 420 Hz and Af/f = 150/570 = 0.26. Since this
component is a harmonic, its amplitude should be well below (about 1/5) that
of the 2UO Hz component. Furthermore, it will be attenuated more by the time
constant filter than the 2^0 Hz component. Consequently, only the 2^0 Hz
component (and the 300 Hz line component) will be considered in the following
analysis.
Let the 330 Hz signal be So and the 2^0 Hz interfering signal component be
N0. From the table it can be seen that the initial signal to noise ratio of
SO/NO is about (1.0/0.6U) = 1.6. The gain of the selective amplifier at 2^0 Hz
is about 0.21 of the gain at the tuned frequency of 330 Hz. The signal to noise
ratio downstream of the selective amplifier S^/Nj. is therefore, (1.6/0.21) = 7.5«
The desired signal Sj_, at the lock-in amplifier input will produce a B.C. signal
output S2 = GX S^ if the synch signal is in phase with S^, where Gx is the lock-
in amplifier gain. The interfering signal, Nj_, at the lock-in amplifier input
will produce a varying signal N2 = &£% (cos ^-^s) whose peak to peak amplitude
equals 2 GxNi and whose rms value is 2 GxNj/{2/2) = GxNj_//2. This signal after
passing through the low pass RC time constant filter is modified so that the
final lock-in amplifier DC signal to rms noise output is
S3 _ S2 i
- --(1+^) -
where cu = 2 n(nf^-f2) = 90 Hz and TX is the time constant of the filter. Assuming
a minimum time constant of 0.01 seconds.
S3 _ GxSi/2
-= —
,
(2n90)2(10-U)]* =7.5/2(5.7) ~ 6l
3-33
-------
Thus, the rms noise components would be no more than 1.6$ (approximately h.Tfo
peak to peak) of the desired D.C. signal even with this short time constant and
would be roughly proportional to the time constant ratio (0.01/T) for other time
constants.
A similar analysis for the 300 Hz harmonic of the line frequency assuming SO/NO ~ Uo
(measured after adding detector bias filter) gives SJ/NI ~ 82 and 83/1*3 = 82 /2
(2.16) = 250 again for TX = 0.01 sec. Thus the rms noise would be about O.h% (about
1.1$ peak to peak)of the desired D.C. signal.
-------
3.3.2 Etendue
For radiometric purposes the geometrical optical property of either beam is
variously known as the optical invariant, An, Lagrange invariant, throughput
or etendue. It is determined by the apertures of the system and their location.
If AI and kg are the areas of the apertures and R is the distance between
them
Alternatively, An may be calculated from the areas of the corresponding
pupils or windows and the distance between the pupils or windows.
In general, it is desirable to locate the apertures in that portion of the
system common to both beams. This is done in the present system for the
emission mode by making the monochromator entrance slit and grating mask the
system apertures. The other optical elements are made large enough so that
their boundaries do not limit the flux. The entrance slit area A;j_(s,h) varies
with slit width, s, and slit height, h. The affective area (normal to the
beam) of the grating mask A2(0) varies as the cosine of the grating angle, 9.
The distance between the apertures is the monochromator collimator focal
length (266 mm). In the emission mode of operation, then, for either the source
or reference beams, the etendue is,
cos e)/F.2
3-35
-------
2
where An = common path etendue cm steradian
c
s = slit width-mm
h = slit height-mm
2
A' = grating mask area-cm
8 = grating angle
F = callimator focal length-mm
c
The grating mask is imaged onto the receiver telescope primary mirror by
the field lens (in front of the entrance slit) and the telescope secondary
mirror. This image of the grating mask is the receiver system entrance pupil
which is similar in shape to the effective grating mask and larger by the ratio
of the telescope focal length to the monochromator collimator focal length.
Af) can be calculated from
2 2
An = A (s,h) A'(9)/F cm steradian
c 1 2 c
2
(s) (h) A' cosG/F
2 C
= (s) (h) (A^ cos6)(F/Fc)2/F2
= (s) (h) (A2cos9)/F2
where F = receiver telescope focal length (= 30^8 mm)
2
A cos9 = entrance pupil area -cm
It was decided that for the emission mode of operation focussing the object
on the entrance slit would require frequent tedious changing of the focus and,
therefore, a fixed focus would be used.
3-36
-------
The boundaries of the field in the emission mode are determined from the
receiver entrance pupil (image of grating mask on receiver telescope primary
mirror), the entrance slit size and the telescope focal length. For an
infinitesimal slit width and height the field boundary is Just the outline of
the entrance pupil which is similar to the grating mask but (30^8/266) times
larger. For finite entrance slit sizes there is a divergence of the beam equal
to the slit height or width divided by the telescope focal length times the
range. The total field width or height is the sum of the entrance pupil width
or height plus the beam divergence.
Maximum values of the field size are shown on Figure 3.3.2.1 for maximum
slit height of 12 mm and maximum slit width of 2 mm. Also shown is the ^ degree
specification value; the maximum field size is less than the specification
value for ranges beyond about 150 meters. Values of the field size for the
focussed condition are shown also for comparison. Note that the full primary
mirror diameter is used for the maximum entrance pupil size.
In the transmission mode of operation reference beam the etendue is calculated
exactly as it is for the emission mode of operation since the apertures are the
entrance slit and grating mask as before. The components of the reference
optical system are made large enough so as not to limit the reference beam.
The etendue for the transmission mode source beam is more complicated as a
result of vignetting caused by the large values of range. One aperture of
the system is the monochromator entrance slit and the other aperture is a com-
posite of the entrance pupil of the receiver system (image of the grating mask,
as before) and the exit pupil of the source system (which is just the net un-
obscured source primary mirror aperture). For an infinitesimal slit height and
width the on-axis etendue for the transmission mode of operation is
dAQ = dA (s,h) A (9)/F2
(ds)(dh)(A cos9)/F2
where the terms are the same as those defined before for the emission mode of
operation. For any off-axis point on the entrance slit, however, the flux is
limited by the exit pupil of the source system. For a point at the entrance
slit sufficiently far from the axis there will be no flux because the pupils
do not overlap (see Figure 3.3.2.2). Consequently all the flux is contained
within a maximum total height (or width) of
3-37
-------
0
0
200
Field Height
Based on Slit
Ht = 12 mm Max
Field Width
Based on Slit
S = 2mm Max
Uoo 600
R Meters
1000
0.6 m
Field Height
L
12mm
____--—t
E
•30^8 ram
Figure 3-3.2.1 Emission Mode Field of View
3-38
-------
Image of
Remote
Receiver
Pupil
Source
Exit Pupil
Receiver
Entrance Pupil
Image of
Remote
Source
Pupil
V2 . D
2DF
V2 w
DX
x =
R-F
DF
R-F
IF R » F
h & h /2 and X = F /R
1 o
Figure 3.3.2.2 Transmission Mode Geometry
3-39
-------
2DF
ho = R
where D = telescope primary clear aperture (= 2k.0 in. = 6l.O cm)
F = telescope focal length (= 120 in. = 30^.8 cm)
H = Range
Actually the maximum imi-s height is slightly less than hQ because the
entrance pupil is slightly sisaller than the primary mirror diameter; the value
of E- is used, for the definition of h^j since it is very nearly equals the pupil
height and represents a limit in any case.
At intermediate points at the entrance slit of h/h (note,0< h/hQ < 1.0)
the etendue will be determined by the overlap of the source exit pupil and the
projected receiver entrance pupil. Figures 3.3.2.3, 3«3«2.U and 3»3»2.5 show
the overlap or net transmitting area as a cross-hatched region for grating
angles of 20, 30 and ^0 degrees respectively for various values of h/hQ. The
areas shown (reduced by an allowance for a 2 mm wide support strut on the
mask) were measured by means of a planimeter and normalized by the net un-
obscured area of the telescope primary mirror. The vignetting factor, V, is
defined
A2(h/hQ, 6)
o
where A (h/h ,8) = net transmitting area of pupils
2 o
A = net unobscured primary mirror area
o
(TrA)(2U2 - 102) = 373.8 in2 = 2^12 cm2.
The values for V are as shown on Figure 3-3.2.6. Here the primary mirror
outside diameter is 2^.0 inches (60.96 cm) and the central obscuration dia-
meter is 10.0 inches (25.h cm).
Strictly speaking the values of V obtained above are for points along the
length of the entrance slit. Slightly different values would be obtained for
points along the width of the slit.
-------
Figure 3.3.2.3 Net Transmitting Area - 9 = 20°
3-U1
-------
Figure 3.3.2.U Net Transmitting Area - 6 = 30°
-------
Figure 3-3.2.5 Net Transmitting Area - 8 = hO°
-------
0
0
Figure 3.3.2.6 Vignetting Factor
3-M*
-------
Because of time limitations and the fact that the vignetting factors in
the two directions are similar,the values along the slit were assumed to be
independent of azimuth (about the optical axis).
A2(r/hQ, 9)
2 22
with r s + h
The etendue for the transmission mode of operation source beam is the
integral within the boundaries of the slit width and height.
= A0(r/h ,9) ds dh/F
t 2 O
= IT A2(r/V 9)
F
Ah2
-^- V(r/hQ, 9) d(s/ho) d(h/hQ)
F
Ah2 h/ho •/>>.
«lt = -^f- I [ V(r/ho, e) d(s/ho) d(h/ho)
F o
Ah2
(h/hQ) v
h/h s/h
where V (s/h )(h/h ) = J J V(r/h , e) d(s/h ) d (h/h )
O O o ° ° °
The integration was carried out numerically using a digital computer.
On the basis of test cases the truncation error i£ believed to be less than
7% (in most cases considerably less). Values of V/cos9 were compared for
various values of s/hQ and h/h and found to be equal within about 5$ average.
-------
It is convenient, therefore, to express Afl as follows for the trans-
mission mode of operation source beam:
An,
2
A h cos9
o o
F2
V (s/ho)(h/hQ)
cos 9
Javg
where A
net unobscured primary mirror area
h = image height = 2FD/R (see Figure 3.3.2.7)
9 = grating angle (see Figure 3.3.2.8)
F = telescope focal length
and the bracketed term is the average integrated vignetting factor, see
Figure 3.3.2.9.
In the transmission mode of operation the ratio (AO /AQ ) is of interest.
t c
This ratio may be written,
A h cos9 V (s/h )(h/h )/cos9
o o 1 ' o ' o Javg
(s)(h)(A2cos9
— V/COS9
avg
This ratio is shown on Figure 3-3-2.10 as a function of (s/h ) and h/h .
-------
Range - KM
2000
Uooo
h =
o
2DF
6000 8000
Range Feet
D =
R =
F =
h =
10000
12000
Telescope Dia = 2 Ft.
Range -Ft
Telescope F.L. = 30^9 mm
Total Image Ht -mm
Figure 3.3.2.7 Total Image Height Vs. Range
-------
1.0
cose
1000
2000
3000
v-cra
-1
sine =
10
2vdcos0
Figure 3.3.2.8 Grating Angle
Grating Norma
3-1*8
-------
S = Slit Width
h = Slit Height
h = Image Diameter :
_
"V = Avg. Vignetting
1.0
h/h
Figure 3.3.2.9 Average Integrated Vignetting Factor
3-1*9
-------
. ...
h/ho
Figure 3.3.2.10 Etendue Ratio
1.0
3-50
-------
3.3-3 Transmission
There are several transmitting factors which control the flux:
1. Transmission of Irtran 2 field lenses and window
2. Reflectivity of aluminum surfaces
3. Transmission of grating
k. Transmission of atmosphere
Irtran 2
There are two Irtran 2 field lenses one just ahead of the monochromator entrance
slit and the other in the detector optical system. There is one Irtran 2
window mounted on the dewar which contains the detector. Each is about 2 mm
thick at the center and since the lenses are weak the thickness variation is
smaJLL. Figure 3.3.3.1 shows the typical spectral transmittance of a 2 mm thick
Irtran 2 element taken from a recent Kodak publication. Also shown is the
measured transmission of the field lens (used at the monochromator entrance
slit) at 0.63 microns. The lower curve for three elements in series was ob-
tained by raising the transmittance values for one element to the third power.
The large variation from sample to sample of transmittance in the visible region
of the spectrum is common among Irtran elements; in the infrared region Kodak
quotes variations of about 2% may be expected.
Aluminum Reflectivity
All of the mirrors in the system are coated with aluminum protected by approxi-
mately a quarter wave (visible) of silicon monoxide. The grating is aluminized
but is not known if a protective coating is applied or not.
Results of reflectance measurements on samples provided by Perkin Elmer
for each telescope are shown on Figure 3«3»3«2.
The reflectance of aluminum protected by a quarter wave (~ 1200-1500^) of
silicon monoxide has been reported by G. Hass and N.W. Scott (JOSA 39 179 (19^9)
and are also shown on Figure 3«3«3«2 as circles.
There are 12 mirror reflecting surfaces in the transmission mode of opera-
tion and 10 surfaces in the emission mode of operation. Both include the
grating as a reflecting surface. Taking the telescope reflectance values as
typical the reflectance values for the system may be obtained by raising the
reflectance value for one surface to the 10th and 12th power. These values
are also shown on Figure 3«3«3«2.
3-51
-------
1.0
.8
.6
.It
.2
0
Wttt
TTT:
;:::
iui
ii
I *Ref. Kodak Publication U-72 "Kodak IRTRAN" (1971)
Three 2mm Elements £j
Mtrtmi
ffi
0
Wavelength -
Figure 3-3.3.1 External Specular Transmittance - IRTRAN 2 (Uncoated)
3-52
-------
-Telescope #1
Telescope #1
1.0
ibiie Surface'
Hass & Scott
JOSA 39 179
(19U9)
10 Surfaces in Series
12 Surfaces in Series
Wavelength -
0
Figure 3.3.3.2 Aluminum Reflectance
3-53
-------
Grating Efficiency
The efficiency of a grating is defined as the monochromatic flux relative
to that for a good aluminized flat mirror used in place of the grating.
Therefore, the efficiency does not include the reflectance of the aluminized
grating surface. Data were provided by the grating manufacturer (Perkin
Elmer) for tools used in the replication process close to the particular
gratings used in this instrument. These data shown on Figure 3-3-3-3 are
for unpolarized input (i.e., polarized at U5° to the azimuth of the grating
grooves). Data for polarizations of 0° and 90° f°r the master grating from
which the gratings used in the present instruments were made are also shown.
Transmission of Atmosphere
The transmission of the atmosphere will include that from normal constituents
as well as pollutants. Molecular absorption from water and carbon dioxide,
as well as absorption from aerosols will be of importance. The exact absorption
for any given setup will depend on the particular existing conditions of
humidity, temperature, aerosol content and size distribution and range (path
length).
For the purposes of this report a clean atmosphere will be assumed;
examples of actual absorption under field test conditions will be shown in
the field test report.
-------
Solid Symbols - Replica Tool
Open Symbols - Master
1000
v-cm
2000
2000
3000 v-cm
1*000
5000
Figure 3.3.3.3 Grating Efficiency Ref. Perkin Elmer
3-55
-------
3.3.^ Modulation Factor
The modulation factor is defined as the zero to peak value of a particular
frequency component divided by the peak to peak value of the total waveform.
For any waveform, the amplitude can be represented by a series.
Cn m
j l_QJ
f(x) = — +V C cos (nx + )
^^j II tl
n=l
27T
where C =71 f(x) dx
o " J
o
2 o 2
27T „ /27T \ 12
C =. /A + B ^ =|/ Tf(x) cos(nx)dx\ + ( { f(x) sin (nx) dx]
n V n n H / / \o
o
0 = tan B /A
n n' n
For a square wave t/T = 0.5 of amplitude, N, for example,
n 2n
CQ = i/ (N) dx + i/(0) dx = N
o n
sin (n7r/2)
Cn ' N (
f, _ TJ / \ _ _ M
Cl ' N ( 2 ) " *
3-56
-------
N
and 0=0
n
Thus for the square wave.
f(x) 12 2 2
-JP = 2 + » cos x - J^ cos 3x + — cos 5x...
The peak to peak value of each frequency component is just twice the value of
the above coefficients and the rms value of each frequency component is (l/v/2~)
times the value of the above coefficients. For the case of a square wave, then:
n C /N = Mod. factor
n'
1 (2/7r) = 0.63662
2/3 TT = 0.21221
5 2/5n = 0.12732
By way of illustration the following description is given of the radiance
variation (neglecting reflection and other losses for now to simplify the
description). Square wave chopping is assumed to make clear the numerical
coefficients.
Consider the case at short range in which the reference chopper is not
running (open). As shown at the top of Figure 3.3.!*.! the total wave form
radiance varies between the hot blackbody source radiance, N ° (A, ^s)> an<*
room temperature (assumed black) chopper wheel radiance, Ny° (X,T ).
w
Let AN = Ns° (XTS) - Nw°(X,Tw)
3-57
-------
Laboratory Case (Ref. Chopper Open)
f (X,Ts)
N° (X,TW;
w w
H(RMS)=
(U/Tl) AN
'
AN
I
_u_
TT
Emission Case
N (X)
s
AN
AN = N (X)-N
N(RMS) =
(U/Tr)AN
- -
Figure 3.3-U.I Single Chopper Modulation
3-58
-------
The first Fourier coefficient (for the fundamental fte*ucncy> f^1" <2/l>
so that the peak to peak variation of the fundamental ***£•*• ^M^T
RMS value of the fundamental radiance variation (U/ir) (AN)/2,/2 - l«W < • '/
^ Jlv/St The selective amplifier selectively passes the fundamental
" and is calibrated in terras of the RMS value of the fundamental frequency
Next consider the emission case in which only the reference chopper is being
used Se total wave form radiance varies between the assumed warm emission
source rTdiance, Ns (X), and the room temperature reference blacKbody radiance,
N ° (X, T ). In this case ^ replaces M^
AN = M (X) - Nr°(X,Tr)
and the same numerical factor of v^as that for the laboratory case appears in the
—:—^^
output,S
this
For the transmission mode of operation dual choppers are, used. In this
. . ^-_*. radiance terms are used for clarity, ngure
preliminary.reference balance and for the
operating'condition for the transmission mode.
mv. i P of N for the »> reference balance is a complicated combination
contain (*,t/A\> '"^f^in the reference balance equations for AN
or absorption. The factor 01 A/C v,«-n««»rt hv both choppers. Although
a. 4-v,^ foo-t- fhflt the source beam is choppea oy ootn (-iiupyc
thirfactor appear! to I arbitrary here, no such «£t£*r^£'e£ni£;* "
the full analysis given previously; this fac or
themselves.
appears
„
also that trns^ssion infor^tion. The
ftcior, must have an extra range of adjustment.
-------
Reference Balance
AT OJL (Source Freq. ) :
N(RMS) = ((V")AN/2/2)
= M^N/2/2
AT u> (Ref . Freq. ) :
Operation
AT UJL (Sovurce Freq.):
AN = [Ns0(X,T8) - N(X,Tw)]
N = (RMS) = ((Vn) AN/2/2) (^)
= (2/rr)AN/2/2
= M^N/2/2
AT io2 (Ref. Freq. ):
AN o ^°(,,Tr) .
N(RMS)= ((V")AN/2/2
= (2/n)AN//2
" M2AN//2
Figure 3.3.1*.2 Dual Chopper Modulation
3-60
-------
The modulation factors of the source chopper, M , and the reference chopper,
MP» are evaluated by means of Figure 3.3.U.3. On this figure are shown the
values of the ratio of the RMS value of the fundamental component to the peak
to peak value of the total signal for both a circular aperture and a rectangular
aperture modulated linearly by alternating open and opaque bands of equal width.
Data for the circular case were obtained from Santa Barbara Research Center.
Values for the rectangular case were obtained from the Fourier coefficients
given in "Reference Data for Radio Engineers" ITT Corporation (19^9) for tra-
pezoidal waveforms.
For the reference chopper the beam width the chopper is about 19nra and
the centerline blade width is about $k.k mm giving D/W~0.55 and M ~0.58
(using the circular aperture curve).
For the source chopper the beam width is from 0 to 2mm depending on slit
width. The centerline blade width is about 8.3mm giving (D/W)^ ~ 0.2k and
HI ~ 0.6^ to 0.62 using the rectangular aperture curve. An average value of
MI = 0.63 may be assumed.
3-61
-------
Modulation Factor =
0 to Peak Fundamental
Peak to Peak Total Wave
Modulation
Factor
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3-62
-------
3.3.5 Spectral Slit Width
For a uniform non-coherent entrance slit irradiance the intensity distribution in
the image at the exit slit may be expressed by an equation derived by
van Cittert* which expresses the image intensity as a function of the image
coordinate x (in the dispersion direction) and the slit width, S. Both x and
S are normalized by the diffraction halfwidth, a, which is the distance
between the image center and the first minimum of the diffraction pattern for
S = 0.
2 .8 x. . 2 .8 x,
sin TT(~ - ~) sin n(~ + ~,
2a a 2a a .
^-> i ~ *_i<-i ^x • i i * '!•* _ ' i r» >_ c^ _» » *
, „.
where Si
. / N C
i (a) = I
J
s •- slit width (entrance = exit)
a = XF/D
X = wavelength
F = focal length of monochroraator collimator
D = aperture = W cos 0 (where W is the grating width)
x = coordinate in image .plane
The image intensity distributions for several slit widths are shown on
Figure 3.3.5.1. It is noted that, for a slit of infinitesraal width, most of the
intensity change occurs over an interval substantially equal to the half width,
a, of the diffraction pattern and the total width of the half intensity points
is also approximately equal to a. For wider slits the half intensity point is
located at approximately x ~ S/2 on the total width 2 x ~ S.
*P.H. van Cittert, Z. Physik 65, 5^7 (1930).
3-63
-------
Dislonce from Imoge Center
Figure 3.3.5.1 Image Intensity Distribution
Distonce Between The Image Center And The Exit Slit Center - -g-
Figure 3.3.5.2 Integrated Output Intensity Distribution
3-6k
-------
Image intensity distributions such as those shown in Figure 3-3«5«l have
been integrated on a digital computer over an interval equal to that of the
slit which produced the image. The resulting integrated output intensity
distributions for several slit widths are shown on Figure 3.3.5.2 as a func-
tion of displacement, XQ, of the center of the image from the center of the exit
slit. It is noted that the half intensity points are located at XQ slightly
more than S/2.
Vhe total width between half intensity points would therefore be slightly
more than G. In the absence of diffraction one would expect from geometry
that the total width between the half intensity points- would be exactly equal
to S.
Therefore, one may consider the total width, 2 XQ, to be composed of two
parts: a geometrical component, 2 xg = S, and a diffraction component, 2 x^
= F(S/a)a.
^g
X
or a
a 2a
2 Xg + 2 xd = S + F(S/a)a
F(S/a)
F(S/a) is defined as the diffraction contribution function and was obtained
by subtraction:
F(S/a) = 2^ - |a
This function is shown on Figure 3.3.5.3.
The spectral slit width is defined as the spectral interval corresponding
to the total width of the output distribution at the half intensity points.
or &v = 2x /— \
o \dx
3-65
-------
U)
ON
CT\
100
NON-COHERENT
ILLUMINATION
0
Figure 3.3.5.3 Diffraction Contribution Function
-------
AX = (S + F (S/a) a) (dX/dx)
Au = (S 4- F (S/a) a) (du/dx)
The grating equation is used to find the grating angle, Q , between the
grating normal and the "bisector of the incident and return beams (separated
by an angle of 20 = 5 degrees, i.e., 0 = 2.5 degrees; see Figure 3.U.4.1).
nX = A (sin i + sin r)
= A I sin (e +• 0 ) ± sin (0 - 0 ) |
= A sin Q cos 0 + cos Q sin 0 ± sin Q cos 0 - cos Q sin0
If n s1 the positive sign is used.
nX = 2A sin Q cos 0
nX
sin 0 =
2 cos0
The angle of the return beam is simply
r cr 0- 0
Differentiation of the grating equation
HA = A(Sin i ± sin r)
with i = Constant gives
— = Acos r
dr
and with dx = Fdr
d\ Acos r
dx = F
Calculations have been made of the spectral slit width for both wavelength
and wavenumber units and the results are shown on Figure 3-3.5.U.
3-67
-------
10
Wavelength -M-
cm
0 I —I-
1000
2000 3000
-1
Waveno. cm
Uooo
8
cm
33 HH
ffif
ffi
88
>i_i^- i.. +-*.
1101 L/MMg
2
Slit Width -
t.TT-
§§§7pQJ
i!
SB
Waveno. cm
Figure 3.3.5.1* Spectral Slit Width
3-68
-------
The parameter dv/ds is of interest when s is considered as a variable in
the analysis of signal to noise ratio. Let Av be the value of Av when
&
s = 0.
Av = (dv/dx) a
a g
Av
a
dR = d(s/a) + d(F(s/a))
dR , d(F(s/a))
d(s/a) ~ d(s/a)
dR d(Av)
ds/a ~ (dv/dx) a(ds/a)
dv _ dv r d(F(s/a))
ds dx g L d(s/a)
When s » a, dv/ds » (dv/dx) ; i.e., the value from the grating equation.
When s = 0 d(F( s/a) )/d( s/a) I -1.00 and dv/ds = 0.
3-69
-------
3.U OPTICAL SYSTEM DESIGN
The optical system consists of the following subsystems in the approximate
order in which they occur along the optical path:
Blackbodies
Telescopes
Reference Optics
Monochromator
Detector Optics
Detector
Synch Systems
The arrangement of these subsystems is shown on Figure 3«^«1 for tne trans
mission mode; for the emission mode the same arrangement is used except that
the source blackbody and telescope are replaced by the emitting source.
It may be helpful to review the system description in Section 3.2 using
Figure 3-2.1.
Each of the above subsystems will be discussed in the following sections
with emphasis on characteristics related to system performance.
3.U.1 Blackbodies
The blackbodies serve as sources of radiant energy for the system which have
known spectral characteristics. Since no other source has a spectral distri-
bution as well known as that of a blackbody no alternatives were considered.
In order to obtain a high signal a high temperature blackbody is desired.
Although there are a number of suppliers of blackbodies for temperature around
1000 to 1200°K only one, namely Electro Optical Industries, makes a black-
body which operates at significantly higher temperatures. One having a maxi-
mum temperature of 1900°K was selected for use in this system; an operational
temperature of 1800°K was selected for increased lifetime over that at 1900°K.
The temperature of the blackbody is controlled by a sensor mounted on the
front plate of the outer housing which activates an electronic control system.
The blackbody housing is cooled by a closed cycle glycol cooling system.
The aperture size was selected to be equal or larger than the system
pupils nearest the blackbody aperture.
3-70
-------
Source & Blackbody
& Modulator
Transmission Mode Shown;
Emission Mode Same Except
Source B.B.& Telescope Not
Used
Field Lenses Are Not Shown
Detector
Source Telescope
Receiver
Telescope
Detector
Optics
Reference
Optics
Figure 3.k.l Optical System Schematic
No Scale
3-71
-------
Prom Figure 3.3.2.2 it may be noted that the image height of the remote
primary mirror, h^ , is the narrowest part of the beam in the transmission
mode of operation and, for ranges large compared to the telescope focal length,
this height is approximately half of the height, ho, at the telescope focus.
At a minimum range of O.U km Figure 3.3.2.7 gives ^ ~ 9.3 mm and therefore
!VL ~ U.7 mm as the maximum field operational values. At small ranges (such
as those used in the laboratory) the height of the source used is limited by
the detector image at the monochromator entrance slit (height = 12 mm maximum)„
Because of the spread of the beam beyond the telescope focus within the
blackbody, the slit height for a small range (such as that in the laboratory)
should be limited to about
For the reference beam the blackbody is imaged on to the entrance slit at
unity magnification so that again 12 mm maximum height is required.
The maximum image width at'either blackbody is 2 mm (equal to the maximum
slit width). However, for large ranges no additional flux is obtained for
slit widths in excess of hQ.
The aperture of both blackbodies was made nominally the same and consists
of an opening about 6 mm wide by 13 mm high with semi-circular ends formed in
the insulating material ahead of the cavity. The cavity was not opened further
(to 13 mm diameter for example) because to do so would degrade the cavity pro-
perties.
The position of the telescope focus was chosen to be at the middle of the
front plate of the outer housing (see Figures 3.U.1.1 and 3.^.1.2). This
position was chosen from consideration of the ray envelopes at the extreme
ranges of O.k and U.O km which are shown on Figures 3.lt.l.l and 3-^.1.2 re-
spectively.
3.U.2 Telescopes
Large telescopes are necessary to maintain system throughput or etendue for the
large ranges specified for the present system. The maximum mirror size (clear
aperture) was specified as 2k inches or less. This size permits an overall
telescope diameter of 28 inches which will pass through ordinary doorways.
The telescope focal length was established by considering the characteristics
of the monochromator (particularly the grating size and collimator focal length),
the variation of telescope obscuration with f/number and the effects of double
diffraction in the monochromator. A focal length of 120 inches (30U8 mm) was
chosen making the overall telescope f/no. = 5«
3-72
-------
Front Plate
Outer Housing
SIDE VIEW
Image of
Remote
Primary
Mirror
h =^. Tram
Telescope
Focus
h «=9.3mm
Approx. Full Size
Telescope
Focus
S=2.0 mm Max
h =k.7mm
TOP VIEW
Figure 3.U.1.1 Source Blackbody and Ray Envelope; Range=0.1*KM
3-73
-------
Front Plate
Outer Housing
SIDE VIEW
Image of
Remote _
Primary
Mirror
h ^0.1+7mm Telescope Focus
h0=0«93 mm
Telescope Focus
S=0.93mm Max
Approx. Full Size
h^ O.U?
TOP VIEW
Figure 3.U.I.2 Source Blackbody and Ray Envelope; Range = U.OKM
3-71*
-------
In order to obtain portability and a compact design, a two mirror tele-
scope design is necessary consisting of a1concave primary-mirror-and a convex
secondary mirror. Several combinations of .mirror surface forms were considered.
These are listed below in order of performance and difficulty of construction.
Primary Mirror Secondary Mirror
".->He,:.;.;aI Spherical Spherical
Sail Kirkham Elliptical Spherical
O:.;?'3-=grain Paraboloidal Hyperboloidal
. , ~ -i
tlitchay Chretien Hyperboloidal Hyp<-rbolcidal
Oo.lc\ui.t.ions oi' the performance of these designs (for a f/1,0 prirr.ar;,'
mirror) were made using the IBM computer "Program for Optical System L°,r.::.T;n"
(or ?OCD). Spot diagrams were made using ICO rays a;nd the size of the sr.'vt
size which contained 90$ of the energy was determined. Calculations were irade
on-axis and at the edge of a 0.25° total field of view. The results of these
4
calculations are shown on Figure 3.U.2.1 by means of open and solid symbols
respectively.
Calculations were also made for the Dall Kir khan: design with f/1.5 and
f/2.0 primary mirrors and those results are also shown on Figure 3,^.2,1.
A criterion of performance is needed with which" to compare tha above data..
The radius of the first dark ring of a diffraction pattern of a circular
aperture is approximately XF/D = X (f/no) which, at the longest, vavele.ri.3th of
13.5 microns and f/55 would give a diffraction pattern radius of about 67
microns or a diameter of 135 microns (within which about <&$ of trie energy
lies). A criterion of 150 micron diameter for 90$ of the energy was adopted.
(to be evaluated at a wavelength in the visible range).
An important telescope design parameter is the ratio of the overall focal
length to the primary mirror focal length; m •- F/Fj_. If the pri.rr.ary mirror
diameter, D, is taken as a controlling aperture this ratio can also be expressed
as m = (D/FjJ/(D/F) = (primary f/no)/(overall f/no). Largs values of m allow
a short telescope but increase the aberrations of the system. Three values
of rc were used in the evaluations as shown in the following list.
3-75 -
-------
1000
Ritchey Cretien
1.5
Primary Mirror f/no.
2.0
Figure 3.^.2.1 Telescope Performance
3-76
-------
m
5
3-33
2.5
Fl
2k in.
36
h8
Pri. f/no
1.0
1.5
2.0
Telescope Length
23.5 in.
30.23
36.0
The overall telescope lengths include an arbitrary 3 inches at each end
for structure and the assumption is made that the telescope focus is 12 inches
beyond the end of the telescope. Figure 3.U.2.2 shows a comparison of these
three f/5 telescope designs (F = 120 and D = 2k inches).
In order to achieve the desired spot diameter of 150 microns it would be
necessary to use the Ritchey-Chretien design with a primary mirror f/no =1.0
whereas at a primary mirror f/no = 2.0 a Call Kirkham design would be accept-
able. Because the primary mirror of the Dall Kirkham design is shallower less
material has to be removed; also the departure from a sphere is substantially
less (approximately 15 times less). Testing of the Dall Kirkham components is
also easier. Therefore, the increased length of the f/2.0 primary mirror
Dall Kirkham design was accepted in order to permit the easier and less costly
construction and testing compared to the f/1.0 Cassegrain or Ritchey Chretien
design.
3-77
-------
f/1.0 Primary
Primary
f/2.0 Primary
Figure 3.*4.2.2 Telescope Length Comparison
3-78
-------
3. If. 3 Reference Optics
The purpose of the reference optical system is to provide a reference beam;
i,e. a becjr. to be compared with that received from the receiver telescope.
The reference optical system contains four reflecting surfaces; the same number
as :.n the source beam for the transmission mode of operation. The components
of t.-;t reference optical system (in the direction of flux) are:
Reference blackbody
Spherical mirror
Flat, mirror
Toroidal mirror
Reference chopper
Iho reference blackbody is nominally identical to that used for the source
r.Mia (see Section 3.U.1) except, that no chopper is employed.
:>;e spherical mirror forms an image of the blackbody (nonu.naJ.ly vnity
at an intermediate focus via the flat mirror.
The toroidal mirror forms an image of the intermediate focus (again nominally
unity magnification) at the monochromator entrance slit via the reference
chopper. The toroid (60° off -axis) was used to reduce aberrations resulting
from the large off -axis angle.
The reference chopper has three blades which are polished and alumni zed
on the side nearest the mono chroma tor. It is set at roughly ^5° so as to
reflect the reference beam on to the entrance slit when a blade is in position
and to pass the source beam to the entrance slit when a slot is in position.
The major optical design problem was that of finding the proper positions
of the elements subject to the mechanical constraints of sturdy and convenient
element mountings, clearance of the beam by structural elements and enclosure
of the system elements for protection.
Provision is made at the intermediate focus for inserting either a blocking
slide or a mercury lamp.
3.U.U Monochromator
The key choice in the optical system design is the means of dispersion since
pollution detection was specified to be by spectral examination of the data;
i.e., pollutants are to be identified by their spectral location and character
and the amount of pollutant is to be measured by the depth of absorption or
emission. The interferometer gives the highest system performance but requires
real-time data conversion by Fourier transformation in order to meet the
specified real-time data display. At the time this system was proposed no
3-79
-------
acceptable data conversion system was available. The alternative dispers-
ing element chosen was a grating monochromator. In the infrared region of
interest prism nonochromators have lower luminosity and filter discs do not
have the specified resolution of about 0.01 micron. A survey of many manu-
facturers of grating monochromators revealed that there was only one commercially
available instrument having the specified linear wavenumber drive, namely the
Torkin Elmer Model 210, which was chosen as the dispersive component. The
alternative of building a grating monochromator was considered to be uneconomical
The optical design of the monochromator had to be obtained from measure-
ment-G since no optical layout could be obtained from the manufacturer even
though exhaustive requests were made. The precision of these measure-
ments was limited because of a desire not to disturb the monochromator alicri-
nient. Since computer runs were to be made using these data the measurements
were adjusted for internal consistency and Figure 3.1*. U.I shows the adjusted
values ur,cd for analysis.
Double Diffraction
A mar:k about 25 ram vide placed along the outside vertical edge of the par-
aboloidal mirror by the manufacturer was removed since it severely restricts
the useful aperture. The purpose of the mask according to the monochromator
manual was to eliminate double diffraction. Double diffraction occurs when
flux strikes the grating twice in its path through the monochromator. From
the geometry it was apparently designed by the criterion set. forth by Chupp and
Grantz* which states that a normal to the collinator surface at the outermost
point on the collimator should miss the grating.
*V. L. Chupp and P. C. Grantz, Appl. Optics 8 925 (19&9)'
3-80
-------
Scale: Half Size
All Linear Dim. in
Off-Axis
Paratolo:
Note: Precision of Measurements ~0.5 to 1 mm; Values
Adjusted for Internal Consistency
Figure 3.^.^.1 Monochromator Optical Diagram
3-81
-------
This criterion is a sufficient condition to prevent double diffraction but
is not a necessary condition for the present instrument. If the normal to the
grating at the inner edge (nearest the slits) misses the paraboloid then no
dispersed flux reflected by the paraboloid can be reflected by the grating
back on to the paraboloid. Such is the case in the present instrument. How-
ever, a certain spectral range of dispersed flux reflected by the paraboloid
can be diffracted a second time at the grating.
Two conditions define the limits of this spectral range of the flux dif-
fracted on the first pass which can again strike the grating. First, the
diffracted flux must strike the paraboloid; the minimum slope with respect to
the grating norml is defined by the line, AB, between the innermost edge of
tho grating (or grating mask if used) and the outermost edge of the parabo-
loid (see Figure 3.^.U.2). The minimum wavelength associated with this slop-;
is designated Xp and for X< X- the first pass diffracted flux will miss tl:o
paraboloid; second, the first pass diffracted flux reflected by the paraboloid
must hit the useful part of the grating; a line, AB, as described above is
extended to the focal plane where the intersection represents the wavelength,
Xcr;, and for X
-------
.Parallel to AB
Figure 3.1<.2.2 Double Diffraction Limiting Incident Rays
3-83
-------
12
10
8
Range of
Rediffracted
Wavelengths
Diffracted
Beam Misses
Parabola
8 10
set
12
Note: Since the bands do not overlap there is no double diffraction
Figure 3.^.^.3 Double Diffraction Wavelength Ranges
3-8U
-------
The fact that there is a gap between the bands of Figure 3«^-^«3 indicates
that a slightly wider grating mask could have been used. The 53 E™ width
chosen is therefore slightly conservative to allow for possible calculation
and measurement errors.
Gr_ating__ Ife.sk
Ons o::' tna system ^perturris is located at the monochroraator grating (the cchcr
:'-.£ at the entrari-c slit). There are two ways in which the aperture nay be
accomplished: l) the beam can completely cover the grating and the rectangular
grating boundary can form the aperture, or 2) the beam can fall entirely within
th-= grating bcu_icLary and a mask on the grating is made slightly more restrictive
chan the beam. The latter method was chosen because a larger area could be
obtained ar.ul bccav.se of double diffraction described above. Completely covering,
r,h
-------
The central mask area is supported by vertical strips 2mm wide in the center
of the mask. The calculated nominal grating mask open area is 15.9 cm .
Entrance Slit
In order to control the aperture at the entrance slit it is necessary to add a
slit height control. A bi-lateral system is used under control of a direct
reading 0-13 nm micrometer. In the transmission mode of operation this slit
height would normally be set to the value of hQ for the particular range of
the set-up (see Figure 3.3.2.7) for maximum energy. For the emission mode of
operation a value of about 12 mm should be used so as to fill the detector;
(i.e., 2 mm x'6). In the laboratory a maximum of about 8 mm should be used
(based en the ray envelope beyond the' focus at the source blackbody just fill-
ing the source cavity).
In the transmission mode of operation a larger slit height than hQ may be usei
to reduce the effects of atmospheric refraction. In this case the value of TSI
-------
Detector
Exit
Slit
90° Off-Axi;
Ellipse
On-Axis
Ellipse
Stem Mounted
Detector
Flat
Detector
"Cassegrain
Exit
Slit
Figure 3.U.5.1 Detector Optical Systems
3-87
-------
Preliminary results using a spherical condenser instead of the toroid
showed a considerable amount of astigmatism. Therefore, the toroid was re-
tained in order to preserve good optical performance. In Irtran 2 field
lens was used to image the toroidal mirror exit pupil onto the "Cassegrain"
center of curvature in order that off-axis rays may be properly controlled.
o
The 90 off-axis ellipse was initially considered for use as the detector
optics system (with reservations, however, because of its suspected large
aberrations). Calculations were made to determine the aberrations using
the IBM computer, "Program for Optical System Design" (POSD). In order to show
system performance two combinations were used corresponding to the two modes
of operation.
1. Telescope System
Source telescope + Receiver telescope + Detector Optics Corresponds
to transmission mode of operation.
2. Dall-Kirkham System
Receiver telescope + Detector Optics;corresponds to emission mode of
operation.
The monochromator was omitted to save time; calculations indicated that
its omission had little effect on the aberrations. The results, in the form
of spot diagrams, are shown on Figures 3.U.5.2 and 3.U.5.3 which show (for
various fractional object heights, OBJH) the location of the intersections of
rays through different portions of the entrance pupil with the image (or
detector) plane.
Calculations for the telescope system were made for the shortest design
range of O.k km which gives an ideal image height of 9.3 mm at the telescope
focus or a height of about 1.55 mm at the detector. For the Dall Kirkham
system the ideal image height is 12.0 mm at the telescope focus or 2.0 mm at
the detector. Note that these spot diagrams include the effect of telescope
aberrations and that there is considerable aberration cancellation,
particularly of coma, when two identical telescopes are used in the transmission
mode of operation. Note also for the transmission mode of operation that the
number of rays is reduced as the fractional object height increases; this is a
result of vignetting.
Calculations for the on-axis ellipse showed the expected better performance
as indicated on Figures 3.^.5.h and 3.U.5.5. However, this system requires
the detector to be stem mounted. After careful study it was decided that such
a detector mounting has a number of design risks. Consequently, this system
was abandoned.
-------
o o
O O O G
Detector Outlire
0.2x2.Omm
Data 6/1U/70-6
1. First Order Image 12mm High at
Telescope Focus.
2. Ellipse Theo. 6:1.
3. Theo. Detector Image 2mm Hich;
Clustered at Heavy Dots.
h. Crosses ere Locations of Chief Kay.
5. hO Rays per OBJH Reach Detector PI-.
O
0 oooooo
-f 4- -+- 4-
0000
-t- -f + -f H- -f-
O O GO
G
-4- H- + -f-
O O O G O
Scale: 1 In. =0. 5mm
G
O
G O
OB.7H
O 1-°
+ '8
0 .6
D .U
X .2
-6- o
X -2
D -.U
0 -.6
+ -.8
O _i.o
Effective
Transmission
Bays
Hitting
Detector
2
2
10
32
UO
32
10
h
'• -J J
Note: 52 Rays Attempted Each 013JK.
- 0.252
572
90° 0.252
Cass.~ 0.629
= o.uo
Figxire 3.1*. 5.2 Dall Kirkham + 90 Degree Ellip.oe
3-89
-------
4-
Scale: 1 in =
Data 6/18/70-2
1. Range = O.h KM.
2. First Order Image = 9.29mm High
at Telescope Focus.
3. Det. Optics Thco. 6:1 Reduction
-f>
0$
-TD
I
)
D
UQ
oc
0
V
•
•
ibf
§fe
^. Tneo. ueTit
Clustered
:t: uui j.iuo.{
at Heavy
^c J. . s stlu
Dots.
5. Crosses Indicate Position of
Chief Ray.
v .
&,_; Detector Q
trim
IrFf P""^. Outline _j_
^Wf*
.L
8P&
c • 'iS
^f itf<
D E
+
0*0
-f t
S 0.2x2. Omm
0
D
X
H 4-
OD
(P X
c> 0 D
0 °
4- +
O
rt.
OBJir
1.0
.8
.6
.u
.2
o
-.2
-.h
-.6
-.8
-1.0
Total
Rays
0
6
10
10
22
ko
22
10
10
6
0
136
Rays
Hitting
Detector
?
2
2
2
20
UO
20
2
2
'4
0
9U
Note: Plotted Pattern Inverted
Because Neg. Object Height Used
Effective
Transmission
_9|_ = Q>6
13°
0.69
Note: 52 Rays Attempted Each OLJII.
-* = 0.16U
572
90° 0.16U
Cass." 0.227
0.72
Figure 3.!4.5.3 Telescope System + 90 Deg. Ellipse
3-90
-------
1.00
Detector
Outline
0.2x2.Omm
0
-1.00
Data 1/25/70
1. Image 9. £9 ram Hiph at
Telescope Focus
2. Dot. Optics 5.326:1
3. Theo. Detector Image 1.7
High;
Rays
Total Hitting
OBJH Rays Detector
+ 1.0
0
-1.0
Uo
26
Scale: 1 in = 0.5mm
Figure
Dall-Kirkham + On- Axis Ellipse
3-91
-------
1.
Data 3/8/70
Image 9.29 mm high at
Telescope Focus
2. Det. Optics 5.326:1
f
i
-*$?-
T
il
- 1.0
,
• D
- .1*
«. I
11
©_
f
II
T
G$&)
A
T
^•> _
— .2
•**^^"
.2
- -.4
_ -.6
_ -.8
1.0
3. Theo.
High;
OBJH
O i.o
4- .8
0 .6
D .4
X .2
Detector "$"
Outline X " • 2
0.2x2. Omm ° "'"J
0 -.6
-f -.8
O -l.o
Effective
Transmission"
Detector
Image 1.74 mm
Clustered at Heavy Dots
Total
Rays
1
5
10
13
22
40
22
13
10
5
1
1U2
1^2
Rays
Hitting
Detector
1
5
10
13
22
40
22
13
10
5
1
142
142 = J-00
Note: 48 Rays Attempted Each
OBJH
I
Scale: 1 in = 0. 5
Figure 3.^.5-5 Telescope System + On-Axis Ellipse
•
3-92
-------
The "Cassegrain" system was investigated with both the Dall Kirkham
tuescope and the Telescope System;, the results ara shown on Figures 3»^
o
She superior performance of the Cassegrain detector system over the 90
ellipse is clearly evident,
30l|.5o8 chews the effect on the detector spot diagrams of adding
. .-onochroniator (vith a fiel^ lens at the entrance slit) to the previou.?
'.1 Xirkhan: + "Cassc^rain" configuration. This configuration represents the
.vl system for the emission node. Only extreme and" central values of olxl^'
j.:t were used to conserve tins. The monochromator spreads tho spot disgvar.
:,y slightly, demonstrating that its omission in the previous runs was not
. iificanto
On, the basis of these results the Cassegrain system v;ns chor.cn for the
ocbor optics«,
>-93
-------
o
CPPD
o
Data 6/1V70
1. Firs- Order "jnage 12 mm High
at Telescope Focus
2. Let. Optics 6:1 Theo.
3. Theo. Detector Image 2 mm High;
Clustered at Heavy Dots
U. Crosses are locations of Chief Ray
5. UO Rays Each OBJH Reach Det. Plane
^O?"'' -'-Tj-K
tJii,:-ji*T^
i^M^^iM"
^^mfr
{••T4!
c^if^
v-.'-'iO
riPSE*
di?&
Detector
• 'sBM?* ^ —
\Wfm^ Outline
§0. 2x2. Omm
jrae*
S^N?*
C "~*\.Sj$~i "1
T«$SSff
(S^!)
/p^m?)
" ^|n J.
t-P^K1"
yr%
»«)
.
0
*
D
X
e
X
D
0
•f
0
OBJH
1.0
.8
.6
.k
.2
0
-.2
-A
-.6
-.8
-1.0
Rays
Hitting
Detector
28
32
31*
36
38
38
38
36
36
26
18
360
Effective
Transmission
360
= 0.818 ~ 0.82
Scale: 1 in = 0.5
Note: 52 Rays Attempted Each OBJH
Figure 3.^.5.6 Dall Kirkham + Detector "Cassegrain" System
-------
1. Ra = O.U Kn.
2. Piri . Order Image 9.29 mm High
at Telescope Focus
3. Dct. Optics Theo. 6:1 Reduction
h. Theo. Detector linage 1.55 ram High;
Clustered at Heavy Ibtr
5. Crosses indicate Position of Chief Ray
I i
i '
I
j
•,
.-
:
fr
A
|^» j kj4f
.
0
Detector
^ Outline
^X 0.2x2.0rm 0
n
ttO^J^n *
Ljgjngip
(fKAUV^
•f^M-
i
1
Scale: 1
•— J
V
D
0
•f
o
in = 0.5™ Elective
OBJH
.8
.6
.4
.2
0
-.2
-.H
-.6
-.8
-1.0
Total
Rays
C
6
10
10
22
UO
22
10
10
6
0
155
?5cr -0.95
Rave
Hitoiru;,
Detectoi
0
6
10
8
20
38
22
10
10
6
0
130
No
Note: Plotted. Pattern Inverted
Becavise Neg. Object
Height Used
Hays Attc-ptod Each 03JK
150
572
'•'•^7
Figure 3.^.5.7 Telescope 3ysten ^ F^tcctor "Cassenrain" Qyn
3-95
-------
o
0
Detector
Outline
0.2x2.Omm
Detector
Outline
Q,Px2.0mm
0
°°
Ooooo0
0°°0
Scale: 1 in = 0.5 nm
Ball Kirkham Tel.
Toroid + Det. Cass.
OBJH = 0, ±1.0
Data 6/lk/70-k
Call Kirkham Tel.
+ Monochr. + Toroid + Dot. Cass.
OBJH = 0, il.O
Data 6/20/70-2
(Incl. Field Lens at Entr Slit)
Figure 3.^.5.8 Effect of Monochromator on Emission Mode Performance
3-9°
-------
3.^.6 Detector
Both mercury doped germanium (Hg:Ge) and mercury-cadmium-telluride (MCT) de-
tectors were considered for use on this system. Considering performance,
methods of cooling and cost it was decided to use the (Hg:Ge) detector.
The size was chosen as 0.2 by 2.0 mm which is the size used by the aono-
chromator manufacturer. Further size reductions would 'require fasv-er detector
optics which would be less efficient than that used in this system.
The field of view of 90 and the location of the aperture mask were chonen
tc be compatible with the "Cassegrain" detector optical system.
3-97
-------
3.U.7 Synch Systems
There are two synch systems (one for the source chopper and one for the
reference chopper) required for use by the lock-in amplifiers in order to
reduce noise.
The source synch is only used in the transmission mode of operation. Part
of the beam from the source telescope is intercepted by the source synch re-
ceiver mounted on the side of the receiver telescope. Signals from this
detector after filtering and amplification are applied to the reference input
of the source channel lock-in amplifier.
Since the signal from the source telescope with the bare detector would be
inadequate at long ranges a lens system was incorporated in the synch receiver.
An objective lens having a clear aperture of about b1? mm diameter and 1^7 mm
focal length is imaged onto the detector (1.5 mm norranal) by means of a field
lens which is a h mm focal length, ^3 x N.A. = 0.65 microscope objective lens.
At very close ranges such as those used in the laboratory and for ranges
below about 200 feet the source telescope beam does not diverge enough to fill
the synch receiver objective. Therefore, a periscope device which picks off a
portion of the main beam has been provided for use in these situations.
The optical diagram for the synch receiver is shown schematically on Figure
3.^.7.1. Details of the synch receiver shown on drawing 596-722-017.
The reference chopper synch signal is obtained from, a photodiode mounted
on the reference chopper housing. It is illuminated by a light emitting diode
(LED) mounted on the other side of the chopper housing so that the chopper
blade passes between the LED and the photo diode. Electrical details are
given in Section 3.6.2 and U.3.2.
3-90
-------
0"bje ctive Lens
/
/ Auxiliary Periscope (used for close ranges)
Synch. Detector
Field Lens
Figure 3.^-7.1 Source Synch Receiver
3-99
-------
3.5 MECHANICAL SYSTEM DESIGN
There are a number of mechanical considerations which can best be described in
relation to the system. These include the stands, the telescopes and the
reference and detector optical system mounts. These are discussed, in turn,
in the following sections.
3.5.1 Stands
The stand is the basic framework which supports the various components and
holds them in proper alignment. The principal design-requirement is to limit
the deflections with minimum weight. Preliminary designs using shells and box
beams wero discarded in favor of a truss framework mainly because the truss
geometry can be easily varied to carry the loads efficiently. The stand size
was limited by the requirement to permit portability particularly within build-
ings. The design width was chosen so as to pass through an ordinary 30-inch
wide doorway. The stand length was limited so as to permit turning in narrow
hallways by removing the telescope assembly if necessary.
Aluminum was chosen for the stand material from consideration of weight and
ease of fabrication. Since all other structure of significant length is made
of aluminum the optical alignment should be preserved as the temperature changes.
It was decided that, for stability in operation, the stand should be support-
ed on three pads. Field adjustment requires a convenient means of adjusting
both azimuth and elevation. A system was chosen in which the stand pivots in
azimuth about ± 1° about the vertical axis of the rear pad by means of screws
on the two front pads which are tangent to an arc centered on the rear pad.
Elevation is controlled over a range of about ± 5° by a screw which allows vert-
ical adjustment of the rear pad. In order to provide the freedom of motion
required for these adjustments each pad is connected to the framework by means
of a ball joint. These also serve to provide adjustment of the stand to an
uneven supporting surface. The centers of the ball joints are the three support
points.
Retractable wheels can be lowered and locked in place to permit convenient
transport of the stand assembly. The wheels are widely spaced so that the
assembly will be stable under any combination of component installation.
The telescope is the largest and heaviest component mounted on the stand.
Although it would have been desirable to support the telescope on both ends this
would have considerably extended the stand length which would have made manufac-
turing difficult. Alternatively, a separate support could have been placed at
the front of the telescope but tliis would disturb the alignment since the loads
would be redistributed. Consequently, it was decided to support the telescope
at its rear face by means of three mounting pads on the stand.
-------
Ibr economy the source and receiver stands are nominally identical.
Because of the additional equipment mounted on the receiver stand numerous
additions to the basic stand were made. These include provision for mount-
ing: 1) the receiver blackbody; 2) the electrical interface panel connections;
3) the prearrplifier; k) the source synch preamplifier; and 5) the mercury
lamp and its power supply.
The source blackbody on the source stand occupies roughly the same position
as does the monochromator on the receiver stand, namely at the telescope focus.
Each should have a complete range of adjustments and therefore a similar
inounting plate is used for each insofar as its attachment to the stand is con-
cerned. These plates may each be raised or lowered by means of three screws.
Each plate has adjustments on the top to permit lateral or fore and aft motion
of the unit mounted; i.e., the monochromator on the receiver stand and the source
blackbody on the source stand. In the latter case, the blackbody is mounted on
a plate having the same outline dimensions as the monochromator. Locking devices
are provided to hold the adjustments.
The exterior of the stands are covered with removable flat panels which
improve the appearance and provide protection to enclosed components. They are
readily removable for service.
3.5.2 Telescopes
The principal mechanical design problems related to the telescopes were the
method of mounting of the primary and secondary mirrors and the method of mount-
ing the telescope as a whole. The mirror substrate selection problem associated
with thermal-mechanical variation of the primary mirror was also considered.
Primary Mirror Mount
Mainly on the basis of thermal considerations aluminum was selected for the
telescope mirror substrate material. At first it was thought to be advantageous
to support the primary mirror at the center hole. However, bending in the
support structure required to transfer the loads out to the telescope mounting
pads was excessive considering the small space available for structure.
The suggestion of the telescope manufacturer to support the primary mirror
by means of tie rods through radial holes in the mirror was adopted after their
assurance that such holes would not cause surface variations. The tie rods
are anchored in a sturdy ring which distributes the loads to the telescope mount-
ing pads.
3-101
-------
Secondary Mirror Mount
Various methods of supporting the secondary mirror were considered including a
truss framework connected to the primary mirror support as well as the more
conventional shell and vane construction. The latter was adopted mainly on
the basis of stability and ease of fabrication.
Telescope Mount
It was considered necessary to make the telescope removable from the stand in
order to pass through narrow hallways. Also, if the telescope ever required
repair or resurfacing of the mirrors, it would be desirable to ship only the
telescope. It was decided to mount the telescope by means of three pads on the
back face in order to ensure stability of the alignment (see Section 3.5.1 also),
So long as the telescope is tested and operated with the operational support
configuration the alignment should be constant (in the absence of vibration).
If vibrations were ever to become a problem a non-contacting dashpot is to be
added below the front of the telescope to provide damping (however, no such
requirement has arisen in the field tests). Of course, material should not oe
laid on the telescope nor should personnel lean on it while in operation.
Thermal Considerations
The effects of thermal expansion on the telescope focal position were investi-
gated as were the effects of thermal expansion on the f<->cal length and form of
the primary mirror.
An equation for image movement at the telescope focus in terms of construc-
tional variations is given in a chapter on telescopes by K. Banner*,
2 22
da = m df-, + (m-l) df2 - m de
where a = distance from secondary vertex to image
m =
f = system focal length
f-j_ - primary focal length
f2 = secondary focal length
e = distance from primary to secondary vertices.
It is noted that df must be negative for a negative secondary focal length.
* Volume 29 of the Encyclopedia of Physics, Springer-Verlag (196?).
-102
-------
The primary mirror vertex is taken as the reference position. The distance
from the primary mirror vertex to the image equals g. From the above relation
then,
dg = da - de
2 22
dg = m df + (m-1) df - (m +1) de
A calculation of thermal effects has been made for the system having an
f/2.0 primary mirror and a +30°F temperature change.
System
da
dg
All aluminum
Pyrex mirrors + zero expans. sep.
Pyrex mirror + Invar separator
Pyrex mirror + aluminum separator
Pyrex mirror + component separator
+ ,01650
+ .01395
+ .01270
- .05^80
+ .00666
+ .00550
+ .01395
+ .01250
- .06580
+ .00550
For an all aluminum system the value of dg = +.00550 is just equal to the
expansion of 15 inches of the aluminum structure. Thus, the position of the
focus relative to the entrance slit does not change with temperature. Note that
the shift of the focus for Pyrex mirrors with respect to the primary vertex,
dg, is negative for an aluminum separator and positive for an Invar separator.
Also the desired value of dg = +.00550 to match the aluminum structure lies
within the range defined by these two values. Therefore, a combination of
aluminum and Invar will match the desired value as shown in the last entry
(~ 91$ Invar; 9% alum.).
On the basis of other thermal considerations (see below) it was decided to
use aluminum substrates for the mirrors. Therefore, the simpler all-aluminum
structure was chosen.
3-103
-------
Several analyses have been made to assist in the selection of a substrate
material for the mirrors. Of particular interest, here, is an analysis show-
ing the difference in temperature between the front and rear surfaces of the
mirror resulting from a different emissivity (i.e., one side polished and the
other not).
The mirror was assumed to be a slab (edge heat flow neglected) having
different surface conductances at each side. Linear heat flow into an ambient
at zero temperature produces temperature gradients. The solution given in
H.S. Carslaw and J.C. Jaeger*, page 126, case 3.11 (ix) has been solved and
run on the computer. The results are shown in Figure 3.5.2.1. Note that the
temperature difference in the case of Pyrex is over 100 times greater than that
for aluminum and the peaks difference occurs at a later time (nearly 20 minutes
after the temperature change). The maximum temperature difference across the
Pyrex slab is about nine percent of the initial temperature difference. Thus,
a 30°C mirror placed suddenly in a 20°C environment would have an initial ATQ
of 10°C and for Pyrex would result in a temperature nearly 20 minutes later at
the polished surface about 0.9°C above that at the opposite face. A similar
aluminum mirror would experience a temperature difference between the faces of
less than 0.01°C.
These results for the Pyrex mirror are used in the following estimate of
the effect on the telescope focus position. Assuming the mirror section to
be bent in a circular arc, the slope change at the edge would be or (ATj_-AT2)/
(L = 5 cm) ~ (3 X 10-6)(30 cm)(0.9°C)/5 ~ l6 X 1
-------
0.1
^-&lAluminum ti:~
Surface Heat Transfer
xlO (cal/sec cm K)
Conv. H =.89 H =.89
Cl C2
Rad. H = .075 H =1.39
Total r 0.965 '2.28
Properties
Alum. Pyrex
K 0.1+8 0.0026 cal/sec cm K
p 2.70 2.23 gm/cm3
c 0.206 0.117 cal/gm K
k 0.86 0.007 cm2/sec
Time - Sec.
AT =Initial Temp. Diff.(from ambient)
o
AT =Temp. Diff. (from ambient) -*~ 0 as time
5 cm. -*•
Polished &
Aluminized
€ = .05
Polished
Figure 3.5.2.1 Temperature Differences in a Slab
-------
Aluminum was chosen over Pyrex for the mirror substrate material for
several reasons:
1. The temperature difference across the mirror thickness for aluminum
is about 100 times less than that for Pyrex (see analysis above).
2. The cost of the telescopes with aluminum mirror, was somewhat less
than that for Pyrex.
3. U»3 of aluminum mirrors allows the whole system to be made of aluminum,
thus simplifying the thermal compensation of the system.
••-:-. Improved technology of metal mirror production*.
P. Experience of others* particularly H.L. Johnson who states "Because
of the^low temperature conductivity of Pyrex, the 28-inch primary warp,
appreciably with changes in air temperature. On the other hand, the
nO^incn , aluminum) telescope's image and focus remain almont constant
with temperature changes, even over the extreme range from daytime to
nighttime temperatures."
2° radial h
Shten "' Three °f the throu^h tole* are used to
on rods extending from a centrai
i a - ***-,*
J +^r aXlal adJUStin^ — *^™ (with rod adjustments)
adjustability of the primary mirror.
_ There ^ was concern regarding the transient thermal response of the aunu
primary nurror because of the differing material thicknes.os. Accordingly,
a,.,,y,e, nave been made to determine the maximum transient difference in tern
mrr°r ^ t0 a ste? chanse in environmental
cho^n T flrSt analySlS radU1 heat flow ™* neglected. Typical sections were
cnosen^at various radial positions (sec Figure 3.5.2.2). Each section was
dzvidea xnto elements and the maximum temperature difference in each section
!!± a di:Rension assumed) ^s determined from a computer run giving the
Svi T h "^ el6ment VSrSUS time- AS GXPeCted' thesc dlfftrLes were
-J-igholy higher than that for a comparable solid slab.
*H.L Johnson vistas Astron. 10, 155 (1968) quoted by F.L. Forbes, Appl. Opt.
7, 1361 (1969) and F.L. Forbes, Appl. Opt. 7, 1*407 (1969).
3-106
-------
Aluminized
Front Surface
(Typical)
Sec. AA
Sec. BB
Sec. CC
3 .
Sec.DD
Figure 3-5.2.2
Telescope Mirror Sectior
for Thermal Analysis
No Radial Heat Flow
Sections Full Size
3-107
-------
Figure 3«5«2.3 shows the data for each section neglecting radial heat
flow. The maximum temperature difference ratio
(AT - AT . )/£T
max min ' °
is at.,-ut 0.0021U for the section at the edge of the mirror (A-A). Not shown
ari? cb.ta for a case in which the holes in the mirror were allowed to ventilate
fby drilling holes from the back of the mirror to connect with the radial holes),
rtj.vi hole ventilation the maximum temperature difference ratio increased to
0.002^7 and consequently this idea was abandoned even though the overall mirror
tics constant vas reduced slightly. It was observed the sections had different
fcize constants which results in a radial temperature potential considerably
in excess of the temperature differential in any section.
The four sections had individual time constants of 9^60, 6?50, 7620 and 5910
seconds for sections A-A through D-D respectively, with an overall average of
7200 seconds or two hours. With these time constants, extrapolation to the
tirr-e of rnaxinuni temperature difference ratio between sections resulted in a
teEperalure difference ratio between sections of (AT^ - ATDD)/ATO of 0.172
at. ac-.-.ut 7200 seconds. Consequently it was decided that an analysis should
be made including radial heat flow.
The second analysis was made including radial heat flow as well as trans-
verse heat flow used before. As shown in Figure 3.5.2.U, a typical mirror
sector was divided into five sections, each of which was divided into five
elements. Heat was allowed to flow between all adjacent elements. External
flux was applied to the front and back mirror surfaces but not to the inner and
outer radial boundaries.
Although there were stability problems in the computer calculations (not un-
conciDn in such analyses), it was possible to obtain data for the temperature
i-.istory which extended to times beyond -that for the peak temperature difference
ratio. Again, as expected, the maximum temperature difference exceeded that
neglecting radial heat flow. However, the increase was nothing like that
indicated by the radial temperature potential described earlier (i.e., 0.172).
The maximum temperature difference ratio between any two eleaents in the sector
was about 0.00266 between element two of section three, and element six of
section two.
3-108
-------
Initial Step Temp Diff.
T - T
Mirror o
0.01
Material: Aluminum
T = Ambient Temp
o
Q.001
0.0001
AT = Max. Temp Diff. (T -T ) of any
max max o
element in the sector
With Radial
Keat Flow
AT , = Min. Temp Diff. (T , -T ) of any
rain min o
element, in the sector
AT = Max. Temp Diff. (T -T )
max v max o
Without
Radial
Heat Flow
in any section element
AT = Min Temp Diff.(T -T )
rain v mm o
Section
!c-c
in any section element
Analytical Solution
for 5 CM Thick Solid-Slab
AT r = Max. Temp Diff. (T^-T_) of
ITicLX
polished side
AT . = Min. Temp Diff. (T -T ) of
mm ' 2
unpolished side
100 1000
Time - Sec.
10,000
3.5.2.3 Transient Temperature Differences in a Telescope Mirror
3-109
-------
Aliuninized
Front Surface "X
(Typical)
5
6
5
6
i
5
6
5
6
^
*
h
4
h
^->
~-v
3
2
3
2
3
2
3
2
5
6
U
3
2
Figxore 3.5.2.4
Telescope Mirror Sections
for Thermal Analysis
Radial Heat Flow Incl.
Sections Full Size
3-110
-------
The determination of the effect of the calculated temperature distribution
on the focal spot condition is very difficult. However, a crude estimate may
be aade by comparison with the calculation made previously for the Pyrex mirror,
in which a fecal shift of O.oUU inches was calculated for a mirror temperature
difference of 0.9°C. With the assumed step change of 10°C in ambient tem-
po raoure
U- - £T . )/£T = 0.9/10.0 = 0.09. The present value of
i''T - AT )/AT of 0.00266 for the aluminum mirror is about thirty
•" mcvx min o
' vv/.'.t) leas.
.'^•sunsliib the focal spot degradation to be roughly proportional to the tcm-
,.-;.ratvjr--: rj-"• France, the degradation with the aluminum mirror should be neglig-
;.*>]..?, perrion:; barely discernible by the most sensitive test. The effect is
pr
-------
In the meantime, however, the relative positions will be determined by the
various time constants of the critical system elements. One can Judge the
change in the position of the focus relative to the entrance slit by compari-
son of the value of dg calculated by the equation below with the value of dg
calculated for the support structure expansion or contraction.
2 22
dg = m df + (m-1) df - (m + l) ds
g = distance from primary vertex to focus
m = f/f1(= 2.5 in this case)
f = system focal length (= 120 in. = 304.8 cm)
f^ = primary focal length (= kQ in. = 121.92 cm)
fg = secondary focal length (= -30 in. = -76.2 cm)
s = distance between primary and secondary vertices (= 30 in. --• ?6.2 err.).
In general, any length element is a function of temperature:
I = 1. + a l.tiS
i i c
where l^ = initial value of i
ATe = T - T± = (T-TQ) - (T.-TO) = AT - AT
T. = initial temperature
T = ambient temperature
Of = coefficient of thermal expansion = 26 X 10"6/°C for aluminum
For t ;> 0, all values of AT± = 1.0 and the values of AT are shown in
Figure 3-5.2.5 as a function of1time. The time constant of each element is
calculated from:
T = cpV/HA
where c = specific heat (= 0.206 cal/gm for aluminum).
p = density (=2.7 gm/cm for aluminum).
H = heat transfer coefficient
3-H2
-------
1.0,
AT
AT
T = Ambient Temp
o
0.01
AT
AT
= Primary Mirror
= Secondary Mirror
= Telescope Shell
= Support Structure (Primary to focus)
0.001
AT
1
_L
2
JL
\
Time - Hrs.
3
JL
5
JL.
6
_L
Figtlre 3.5.2.5 Temperature vs. Time of Telescope Elements
3-113
-------
V/A = geometrical factor
= t /2 for a thin disk
avgr
= t /2 for a thin shell
s
== t/U for support structure (with only the outside surface involved
in heat transfer).
Element
Primary mirror
Secondary mirror
Telescope shell
Support structure
20
H (cal/cm Ksec)
avg
1.62 X 10'^
1.62 X 10-1*
2.28 X 10"1*
2.28 X 10"1*
V/A (cm)
2.9
0.6
0.08
0.08
~" T (sec)
10,000
2,060
195
195
T (hr)
2.78
0.57
0.05^
0.05^
The lower value of H for the mirrors results from the low emissivity of one
surface.
The change in length can be expressed as:
= a
\ - 1)
3-nU
-------
Using these data the change in the focus is
[/ "^1 \1
yf,AT (e - 1]
\ /J
- (7.25)
The change of the entrance slit position (relative to the primary mirror)
will be governed by the expansion of the support structure:
dg'=
{•
The relative position of the focus and entrance slit is determined by
dg - dg' which is shown on Figure 3.5.2.6 for a change of ambient temperature
AT = 1°C. The peak shift of the focus relative to the entrance slit occurs
about lU minutes after the temperature change. If the change occurred at the
beginning of a lU minute run, the effect of the change, if significant, would
be detected in calibrations before and after the run. Changes in the system
after about 15 minutes take place quite slowly, and would therefore have less
effect (about twenty times less) on calibration change during a run.
From the magnitude of the effect it is judged that these thermal changes
will not be significant with the aluminum mirrors.
3.5.3 Reference Optical System Mounts
There are two features of the reference system mounts which are related to system
requirements .
Provision is made in the mounting of the spherical mirror for its removal
to permit insertion of the radiation probe into the reference blackbody in
order to check its radiance whenever desired. The mount for the spherical
mirror is strictly kinematic to assure precise positioning.
Provision is also made at the intermediate focus for inserting a blocking
plate to block the reference beam during initial set-up. It is also possible
to mount a mercury lamp at the intermediate focus for alignment and/or calibra-
tion purposes.
-------
-.020
lU Min.
-.015
-.010
dg - dg'
(cm.)
-.005
.0152 cm(.006 in.)
1U Min.
AT = 1°C
o
Time - Hrs.
dg = Focus Pos. Change
dg' = Ent. Slit Pos. Change
Figure 3.5.2.6 Difference in Position of Focus & Entrance Slit
3-H6
-------
3.5.1* Detector Optical System Mount
The mounting of the detector "Cassegrain" involved consideration of not only
alignment of it and the detector but the installation of the detector as
well. The detector is mounted on a slender cold finger within a dewar to
protect it from the atmosphere. The dewar is attached to the refrigerator
cold head. There are two flexible hoses connected between the c.old head and
the compressor .(in the auxiliary stand). These lines may exert a consider-
able force on the dewar and its mounting; therefore, the dewar mounting must
be quite rigid. Although it would be desirable to have fine adjustments on
the location of the detector (and therefore the dewar) it is difficult to
construct these adjustments with sufficient rigidity. Consequently it was
decided to provide only lateral adjustment of the detector-dewar assembly and
to provide for the more precise focus adjustments in the mounting of the
"Cassegrain" assembly.
3.5.5 Detector Cooler
The major mechanical problem associated with the detector cooler is
vibration.
The most suitable closed-cycle coolers, in terms of performance and price,
are produced by Malaker and by Cryogenics Technology (formerly 5CO Inc.), a
subsidiary of A. D. Little. Representatives of both companies brought in samples
of their coolers for demonstration. The Malaker unit was available for a
week to allow evaluation.
In addition to the demonstrations and tests, the choice of coolers was dis-
cussed with several users of these devices in other aerospace companies and in
government laboratories and with detector manufacturers who integrate the detector
with the cooler. These evaluations indicate that there is a vibration problem
associated with the Malaker cooler.
A number of tests were made with the water-cooled Malaker unit to determine
the approximate amplitude of vibration with a calibrated microscope. With
the cooler mounted on blocks as recommended by the manufacturer, the peak-to-
peak deflection was about 30 microns, regardless of the mass attached to
the system. The cooler was attached to a model 210 monochromator by means
of a 3 x 3 x f inch aluminum angle with the cooler hanging vertically down-
ward over the edge of the bench. Observations on a plexiglas window showed
a deflection again of about 30 microns peak-to-peak. Various attempts to
reduce the vibration by clamping the monochromator to the bench with large
C-clamps and/or restraining the body of the cooler produced only a small
reduction, if any, in amplitude. Finally, the monochromator was clamped to
a large, heavy (approximately 2000 Ib) surface plate; the window and the
3-11?
-------
cold head vibrations were slightly less than 30 microns and in different
planes, The cooler was removed from the monochromator and weighted down
and clamped in blocks onto the surface plate. The deflection of the
cooler was more than 100 microns; the surface plate vibration was roughly
30 microns peak-to-peak. A check was made to ensure that the observed
motion was not that of the microscope by observing another tripod with
the cooler operating; no motion was observable. From these tests it was
concluded that the vibration would not substantially be reduced by addition
of mass to the cooler. In a subsequent discussion Malaker representatives
agreed with this conclusion.
Consideration was next given to means of isolating the cooler vibration
from the detector and the pedestal structure. This requires mounting the
cooler on vibration isolation mounts (a separate support was judged opera-
tionally unacceptable) and providing low transmission couplings for the
vacuum jacket and the detector heat flow path. Various opinions were
obtained from persons familiar with vibration problems from which it was
concluded that an appreciable technical risk would be involved in the
isolation approach.
As a result, the alternative higher priced ADL cooler was considered
more closely. The model 0125 is a relatively new 60 cycle version of a
cycle model 0120 cooler, which was demonstrated.
In the demonstrations it was observed that the vibration of the model
0120 refrigerator was markedly less than that of the Malaker unit. These
observations and experience of others indicate that the. vibration levels
of the ADL cooler are an order of magnitude less than those of the Malaker
cooler and are acceptable for the present application.
The Cryogenics Technology representatives indicated that vibration of the
model 0125 refrigerator would not be greater than that of the model 0120.
Later, a vibration test of the CTI cooler, Model 0125, was made at Convair
under operating conditions.
With the refrigerator head C-clamped to the edge of a bench, a vertical
motion of the relection of a laser beam from a mirror mounted on the re-
frigerator of about 1/32 inch pp was observed at a distance of about 20 feet
(beam deflection ~ 1.1 mrad or mirror deflection ~ 0.6 mrad peak-to-peak).
A screwdriver placed between the refrigerator and the bench reduced this
deflection so as to be undetectable. The refrigerator case was observed with
a microscope to move about 3 to 5ji, with or without the screwdriver brace
(operating temperature ~ 15 K) .
3-118
-------
The cooler was next C-clamped to a light stand (1 x 1 x $ angle
2U x 3U Inches on four legs •& O.D. x 0.09 wall pipe — 26 inches long,
with no bracing). Again, a motion of three to five microns was observed.
Restraining the compressor hose, about four feet from stand, Increased
the vibration about 50 percent.
The refrigerator was then C-clamped to a stand 3** x 60 x 36 inches
tall, made mainly from 3 x 3 x £• Inch aluminum well braced. The motion
of the refrigerator case was less than 3n, peak-to-peak.
The cold tip was next observed using a glass pipe dewar and a plexiglas
end plate. No vibration was observed with the vacuum pump operating. Initially,
at room temperature, with compressor outlet/inlet pressures of 390/50 psig, a
deflection of about UOn ± 10^ of the cold tip was observed along the motor axis.
If the compressor was turned off and the Ap reduced (~ 110/110 psig), the
vibration reduced below the limit of detectability (~ 6p.). With a hydrogen sensor
pressure of about 7 psig (~ lB°K) at the cold tip and compressor pressures of
260/100 psig, a deflection of about 20(J. ± 7 ^ of the cold tip (along the motor
axis) was observed. Manufacturer specifications state that the refrigerator motor
speed is 200 rpia (equivalent to 200/60 ~ 3.3 cycles/sec). This was roughly the
observed frequency.
The vibration which we observed does not appear on the vibration spectrum
of a similar prototype Model 0120 cold tip. The manufacturers representative
stated that vibration spectrum supplied by CTI was run without the coripressor
attached; thus accounting for the absence of the observed operational vib-
ration. CTI personnel are currently considering a re-design of the cold-finger
to reduce the vibration level.
Results of vibration tests made at CTI vere received by telephone from CTI
which explain the above observed cold head vibration data. Initial tests at
CTI confirmed our results. It was found that the mounting flange was attached
to the refrigerator via an 0-ring (not in a groove), thus allowing freedom not
present in normal installation. Further test at CTI after correct instal-
lation gave the following peak-to-peak vibration results for the cold finger:
Operation Ax fly Az
Refrigerator only Operating 3& Iji O.lji
Compressor and Refrigerator 5u 3u 5H
Operating
Ax is along the refrigerator motor axis (others not defined)
3-H9
-------
These results were obtained by eliminating the 0-ring and operating the
system without a dewar and, therefore, the cold head was not at operational
temperature. However, there is little doubt that similar results would be
obtained at operating temperature.
The above data are judged to be satisfactory and the CTI model 0125
cooler was selected for use in the ROSE system.
3.5-6 Detector
The mechanical configuration of the detector is shown in the specification
drawing Figure U.I.6.1. The detector mounting details are shown in the
Component Details Section U.2.9«
3.5.7 Synch Systems
The major mechanical system requirement for the synch systems is for a
sturdy mounting of the sensitive elements. Details of these mounting arrange-
ments are given in Component details Section U.2.11.
3-120
-------
3.6 ELECTRONIC SYSTEM DESIGN
3.6.1 The Electronic System
The electronics system is defined to be all aspects of instrument components
that perform an electronic function, as well as the electronics associated
with cornponent.s that serve a mechanical or optical function. An exazrple of
CK-E-oncrits that are mechanical in nature are the choppers. The chopper motor
clvivc circuitry and electrical characteristics of the motors is covered in
the electronic system description. However, the function, mounting, physical
characteristics, etc., of the choppers will be found under the mechanical
description. An electronic component such as the signal preamplifier would
bo described as to function, electrically, and mechanically in the electronic
system.
The system design section is limited in scope to an operational description
of the electronics. It is intended to give the reader a systems understanding
and operational capability. Circuit descriptions, schematics, troubleshooting
procedures, physical dimensions, etc., are covered in the electronics system
details portion of this document.
The system has been divided into seven subsystems and both the system
design discussion and system details section are divided into these seven sub-
systems: Signal Sources, Signal Amplifiers, Wavenumber Generation, Data
Aqmsition, Data Recording, Electronic Calibration, and Power Subsystems.
3.6.2 Signal Sources;
There are five (5) signals associated with the instrument; source (l), Reference
(I0), source synch, reference synch, and wavenumber. These are grouped below
according to the source from which they are derived.
Source and Reference - Hg:Ge
The source (I) and reference (Io) signals are both generated by the cooled
HgrGe detector. The output of the mercury doped germanium (Hg:Ge) detector in
the transmission mode of operation of the instrument is a combination of (I)
and (I ) signals. The magnitude of the (I) portion of the signal is determined
by the intensity-of the chopped remote blackbody and the atmospheric path.
The frequency of the (I) signal is determined by the variable speed source
chopper. The magnitude of the reference portion of the signal is determined
by the intensity of the reference blackbody and its frequency by the fixed fre-
quency reference chopper. When the instrument is operating in the emission
-------
mode, there is no reference (IQ) signal, or blackbody sources. The source of
signal now becomes the atmospheric or pollutant emission. Output of the Hg:Ge
detector in this mode has an amplitude proportional to the emission and a
frequency equal to the reference chopper frequency. The low level nature of
these signals requires narrow bandwidth amplification and detection to produce
an adequate signal to noise ratio. This requirement generates the need for the
source and reference synch signals.
Source Synch
This signal is used as a frequency and phase reference for the source lock-in
amplifier. The source synch signal is produced by intercepting a portion of
the signal beam and focusing it on an Indiun Arsenide (InAs) detector. This
signal will have the same frequency as the source (I) signal and will have a
fixed phase relationship to it. It is used only when the instrument is operat-
ing in the transmission mode.
I
-------
Source and Reference Amplification
The source (I ) signal must be linearily amplified and rectified in a narrow
band amplifier. The mixed signal (I) and (IQ) output of the cooled detector
is first preanplified. The preamplifier is a Princeton Applied Research
(P.A.R.) variable gain general purpose broadband preamplifier. The output of
the preamp is coupled through the standard signal-operate switch to two selective
amplifiers. The selective amplifiers are P.A.R. narrowband amplifiers that
provide for center frequency adjust, gain selection and variable "Q". These
amplifiers each selectively pass the preamplified signal components at the source
chopper frequency or reference chopper frequency. The output of the selective
amplifiers serves as the input to the lock-in amplifiers. The lock-in amp-
lifiers are modified P.A.R. Model 220 amplifiers. The amplifiers provide for
center frequency adjust, sensitivity, time constant selection, and phase adjust.
Ths center frequency adjust tunes the lock-in amplifier to the synch signal
frequency; the time constant control determines the instrument bandwidth; the
sensitivity selection controls the gain of the lock-in amplifier. The phase
control adjusts the phase of the respective synch signal to coincide with the
phase of the signal. The resultant effect these amplifiers have on the signals
is to convert them to narrow bandwidth d.c. voltages. The modifications made
to the P.A.R. 220 lock-in amplifiers have altered some parameters displayed on
the front panel. The panel has been changed to conform to the new values of
time constant and sensitivity. The output impedance of the lock-in amplifiers
is 5K ohms. The next operation to be performed on the signal requires a low
so\irce impedance. This necessitates the insertion of unity gain amplifiers.
The unity gain amplifiers are integrated circuit amplifiers that share a circuit
board with the compensation amplifiers. They are a Convair design and are
located in the logic chassis. They provide the low driving impedance the com-
pensation amplifiers require for accurate gain determination. The compensation
amplifiers are used to compensate for the effects on the signals due to the
sharing of a common chopper. Since both the source signal and reference signal
are chopped by the reference chopper the source signal is reduced (nominally
one-half) compared to the reference signal. The source compensation amplifier
restores the source signal to its proper level and provides the adjustment
necessary to calibrate the electronic gain. Calibration is accomplished by
adjusting the input of the source compensation amplifier with a potentiometer
mounted on the control panel. Proper source channel gain is provided by a gain
equal to eight. Under the condition where the atmospheric absorption is equal
to zero, a combination of the potentiometer set at £ of maximum, a gain equal
to eight would yield the proper source signal level assuming no vignetting.
-------
The reference compensation amplifier is a differential amplifier with
unity gain. The output of the reference channel voltage follower drives
the inverting input while the source channel voltage follower drives the
non-inverting input. The reference compensation amplifier output is set to
zero with the reference beam blocked in an initial set-up procedure. This
makes the reference compensation amplifier output independent of source signal
variations. With the block removed from the reference beam the output of the
reference condensation amplifier depends only on the reference beam. See the
radiometry Section 3.3 for a more detailed description. Further processing
of the signals is accomplished in the data acquisition system.
Synch Signal Amplification
There are two synch signals; the source synch and reference synch. These
signals are required by the respective lock-in amplifiers as their reference
input. The reference synch amplifier is the simpler of the two. The method
used to generate this signal provides a relatively high-level signal. Con-
sequently, the reference synch detector can drive an integrated circuit opera-
tional amplifier directly. In this case it is an amplifier with a gain of one
thousand that is driven into saturation by the synch signal. The band-
width of the amplifier is constrained from 200 Hz to 1300 Hz for the purpose
of avoiding the amplification of the noise that appears across the high im-
padance input. The narrow band feature of this amplifier is, however, of no
consequence as the reference chopper that generates the signal is fixed in
frequency at approximately 330 Hz. Source synch signal amplification is much
raors difficult because in a long path length condition the detected signal may
be as low as 0.7 microvolts. Additionally, the variable nature of the source
chopper requires that the amplifier have a wider bandwidth. To satisfy these
requirements, it was necessary to first transformer couple the signal into a
preamplifier. The transformer provides voltage gain and matches the low im-
pedance detector to the high input impedance of the preamplifier. The pre-
amplifier is a three-stage, discrete component, JFET amplifier with a gain of
500. Due to the fact that the power supply voltage used to power the L.E.D.
contains 120 Hz ripple, this frequency presented a special difficulty. The
insertion of an integrated circuit amplifier connected as a 120 Hz gyrator in
the signal line at this point provided sufficient 120 Hz rejection. A line
driven amplifier follows the gyrator; it amplifies the signal to a level such
that the signal may be transmitted by coaxial cable from the receiver stand to
the electronics console. Inside the electronics console the signal is further
amplified into saturation. This is done in two stages: The first stage is a
low pass amplifier with gain equal to ten thousand (10K), and the second stage
is a high pass amplifier with gain equal to one thousand (IK). The net result
-------
is an amplifier that saturates at the lowest level of detected synch signal
with a bandwidth from 3^0 Hz to 720 Hz. The two synch signals now are identi-
cal except in frequency. They are square waves with ±15V swing which will
provide a phase reference to the lock-in amplifiers and drive the standard
signal generators.
3«6.U Wavenumber Generation
In the discussion of signal sources it was mentioned that the wavenumber was
generated by a shaft encoder mechanically ganged to the grating drive mechanism.
The number of pulses the encoder generates is nine thousand (9K) per shaft re-
volution. However, the information required is the actual wavenumber to a
resolution of 0.1 wavenumbers. This is accomplished by feeding the 9K counts
per revolution into logic circuitry that converts them to the number of 0.1
wavenumbers per shaft revolution. These output counts from the logic are added
to the count or actual wavenumber displayed on a counter. The logic scheme is
somewhat complicated by the fact that there are two gratings and the number of
wavenumbers per shaft revolution is not only different for each grating but may
also be a function of the alignment of the monochromater and the environment.
This complication is handled by making the output of the logic circuitry
selectable from the control console. Hence, depending on the grating in use
and the wavelength calibration, the proper number of 0.1 wavenumbers per re-
volution may be selected from the control console. The logic circuitry is
divided into a number of sections depending on the function served. Each will
be functionally discussed here and detailed further in the electronic system
details section.
Pulse Shaping Logic
The pulse shaping logic has as its input the clockwise (CW) and counter-clock-
wise (CCW) pulses generated by the shaft encoder. The logic first examines
the pulses and makes two decisions. First is the pulse a noise spike or real
pulse? Second is it the second consecutive and non-coincident pulse indicating
motion in one direction? If these conditions are met, it then enables a gate
that drives the coarse range counter and a monostable multivibrator. The mono-
stable multivibrator delays this pulse and then drives the fine range counters.
The reasoning behind these operations is based on the fact that vibration of
the encoder may cause it to generate noise pulses. This circuitry takes advant-
age of the fact that these noise pulses are often coincident or alternating
on the CW and CCW lines and differ in duration from real pulses. Hence the
result is a successful separation of noise and actual rotational pulses. The
fine range counters inputs are delayed so no coarse counter output and fine
counter output will be coincident and therefore lost to the output.
-------
Direction Sensing Logic
The direction sensing logic senses CW or CCW rotation of the encoder which
corresponds to increasing or decreasing wavenumber respectively. This logic
function then serves two purposes. First, it steers the output of the logic
to the (X) or (Y) input of the bidirectional counter where the (X) and (Y)
inputs are the up and down counting inputs of the counter respectively.
The other use of the direction sensor is to enable the data resolution
counter. To avoid possible backlash problems, data is acquired only when the
instrument is scanning up in wavenumber. Hence, only CW (i.e., increasing
wavenumber) counts are enabled into the resolution counter which generates
acquisition of data commands.
Counting Logic
The purpose of the counting logic is to take the incoming 9K pulses per re- ^
volution and divide by a number such that the output equals the number of 0.1 cm
per revolution. This is accomplished by the use of three (3) counters, summing
gates, count selector switches and counter reset gates. The three counters are
called the ones, tens and coarse counters. Each counter operates independently.
The coarse counter is driven directly by the pulse shaping circuit, while the
fine counters are driven by these same pulses delayed U microseconds. The ones
counting logic outputs from 1 to 9 counts per revolution in unit steps. The
tens counting logic outputs 10 to 30 or 80 to l60 counts per revolution in
steps of ten. The coarse counting logic outputs $00 or 529 counts when the
instrument is operative in the 7 to 13.5 micron region and 1125 or 1286
counts per revolution in the 3 to 5.5 micron region. The ones, tens and
coarse selector switches on the control panel select the number of counts which
appear at the output of its respective counting logic. The summing gates are
HAND gates driven by the proper 2N outputs of the counters so that there is a
gate whose output is one of each of the required outputs from each counter.
The output of each summing gate is tied to a pole of a multiposition switch.
The wiper of this switch goes to an inverting gate and to the counter output
logic. The inverting gate is in turn reinverted and connected to the reset lines
of its counter. The purpose of this double inversion tied back to the reset is
simply to delay the counter reset so that the output at the switch wiper will
have sufficient pulse width to enable gates in the counter output logic. In
summary the counting logic has as its output three lines: ones, tens and _^
coarse counts. The arithmetic sum of these would be the actual number of O.lcra
per revolution if the selector switches were set properly.
3-126
-------
Counter Output Logic
The counter output logic input is the output of the counting logic that appears
at the selector switch wipers. A two-level or gate sums the pulses for the
total count per revolution. The total count goes to either the (X) or (Y)
input of the bi-directional counter as directed by the direction sensing logic.
The total (X) count also serves as the input to the resolution selector logic.
Re solution Selector Logi c
The resolution selector logic consists of a bindary counter, summing gates,
a selector switch, and a line driver. The purpose of the resolution selector
is to allow for the option of the spectral resolution element at which the
data will be outputed. The selector switch allows for resolution elements of
0.1, 0.2, 0.3, 0.5, 1 and 2 cm""1. When a resolution of 0.1 cm"1 is desired
all of the counting logic (X) output pulses are inverted and connected to a
position on the resolution selector switch. When resolution less than 0.1 cm"1
is required a counter gate and summing gates divide the 0.1 cm"1 pulses by the
proper factor and the summing gate outputs are wired to the various selector
switch positions. The output of the resolution selector switch (wiper) is in-
verted and then drives an additional inverter and a monostable. The double
inverted pulse is used to reset the resolution counter with the small inherent
delay.
Data Control Logic
The monostable is used to provide sufficient pulse width to drive the data con-
trol output. The data control output is the signal that commands the data
acquisition system to take a reading. It must drive two instruments, the data
coupler and the sample-hold digital volt meter (D.V.M.). The input pulse width
requirements of these instruments dictated the use of a monostable. Addition-
ally the drive requirement of the coupler requires that the monostable output
drive a Darlington emitter follower as its input impedence is approximately
50 ohms on the read input line. The combination of the monostable and Darling-
ton amplifier are jointly referred to as the data control logic.
3.6.5 Data Acquisition Subsystem
The purpose of the data acquisition subsystem is to convert and format the out-
puts of the instrument into signals acceptable to the data recording subsystem.
This means that the counts representing wavenumber must be counted and con-
verted to Binary Coded Decimal (BCD). The ratio of the output of the source
:orapensation amplifier to that of the reference compensation amplifier must
be calculated to yield transmission (T); both analog and BCD representations
3-127
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of (T) are required. Additionally the source compensation amplifier output
must be sampled coincident with particular wavenumbers and converted to BCD.
There are four (U) signal converters in the data acquisition subsystem.
They are: a presetable bi-directional counter, a ratio D.V.M., a sample-
hold D.V.M., and an analog ratio module. These converted signals must then be
put into the proper format and timed to the recording units. For the digital
data these functions are performed by the data coupler.
Wavenumber Conversion
This conversion is made by the bi-directional counter an Anadex Model CB-600R
with preset zero, preset count level, BCD output and "Readout on the Fly"
options. The counter has two inputs (X) and (Y) and is operated in the (X)-
(Y) mode. The (X) or C.W. output of the wavenumber generator logic goes to the
(X) input of the counter and (Y) or C.C.W. logic output to the (Y) input. The
resultant count due to grating motion is the net equivalent number of 0.1 cm'1.
If the preset zero switches are used to set the initial value of wavenumber
the result is the actual wavenumber. The normal method of operation is to set
the monochromator to a known wavenumber, set the preset zero switches to the
number and press reset. Then during the scan the counter reading will increase
in value to the end of the scan. The monochromator is then hand cranked back
and the counter will track down. The BCD option converts the count appearing
in the windows into BCD logic level voltages at the rear output connector.
The BCD output is required as an input to the printer and digital tape recorder.
The "Readout on the Fly" option allows the counter to internally track the count
without changing the reading in the windows or output. This is necessary be-
cause the time required to record and/or print may exceed the time required to
scan to the next 0.1 wavenumber. "Readout on the Fly" effectively holds the
counter reading while data is being recorded and then updates the counter output
to the actual value when the data recording cycle is completed.
Source Digital Output Conversion
The output of the source compensation amplifier will usually change rapidly with
wavenumber. Consequently the time at which a reading is made of the value
should coincide precisely with the indicated wavenumber. This dictates the use
of a sample and hold technique on the reading. A Dana Model 5^03-015 digital
voltmeter is used in this system to provide both the voltage resolution and high
speed sample and hold required. The pulse on the data control line from the
logic box that commands data output to the printer or recorder also enables a
read to this D.V.M. Hence, the D.V.M. reading and wavenumber indicated on the
counter correspond. The data coupler in turn inhibits a change in counter or
D.V.M. reading until all the data has been outputed to the printer and/or
recorder. The D.V.M. converts the D.C. voltage at the output of the source
compensation amplifier to BCD with ten (10) volts being full scale and with four
(U) digits of resolution plus over-range of 10$.
-------
Transmission Coefficient (T) Digital Output Conversion
A Dana Model 5U03-010 is used to convert the outputs of the source and reference
compensation amplifiers into the BCD value of transmission. This is done by using
the voltmeter in its ten (10) times ratio mode with the voltmeter reference being
the reference compensation amplifier output and the input being the source com-
pensation amplifier output. The result is a voltage which is 10 volts full scale
resolved to four digits plus over-range that equals ten times the transmission,(T).
The BCD conversion for this instrument requires approximately 2ms during which time
the input may change. The source input can change much more rapidly than the
reference input. This fact suggests the operation of the instrument in a mode that
would provide a higher accuracy than the normal mode. The source signal is applied
to the 5U03-015 D.V.M. in the normal manner but the reference signal is applied to
the 5U03-010 DVM input, the latter being put in the FAST DC mode. The system would
then have one D.V.M. measure the source and the other measure the reference. Since
the slower D.V.M. would be measuring the slowly changing reference the results would
be more accurate. The ratio of the source to the reference signal would be cal-
culated externally to the sytem (in a computer, for example).
Another feature of this D.V.M. that is useful in the system is that in the READ mode
it need not be commanded to read. Therefore, for set up, calibration and trouble
'shooting it may be used as a voltmeter. In the system it is in the HOLD mode and
is commanded to read and the reading is held by the data coupler. When not in the
hold mode this D.V.M. continues to read at k readings per second.
Analog Ratio Module
The analog ratio module is a unit designed by General Dynaiaics/Convair to pro-
vide transmission coefficient, (T), in analog form for display on the strip chart
recorder. The circuit is designed around an integrated circuit multiplier-
divider, and its recommended circuit. The resultant ratio is accurate to about
± 2% for a large reference signal. While, not as accurate as the digital ratio,
it is more than adequate for the analog display which is not intended to be
used for analytical work. The inputs to the ratio module are the same compensa-
tion amplifier outputs that serve as inputs to the ratio D.V.M., therefore the
analog and digital ratio are equal at all times within the accuracy of the
instruments. The output of the analog ratio module is connected to a switch
called "strip chart input selector" located on the monochromator control panel.
This switch allows for selection of source, reference or ratio input to the
strip chart recorder.
Digital Data Coupler
The digital data conversion instruments have an output of thirteen BCD characters.
The counter has five characters representing wavenumber. while each D.V.M. has
four characters one character set for (T) and one for source (I). The data
coupler on command causes these 13 characters to be recorded on the digital tape
3-129
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recorder and/or the digital printer. The data record sequence is started by
a data control output pulse from the logic box which is coupled through the
control panel to the data coupler. The data coupler in turn commands the
D.V.M. 's to take a reading and holds the counter reading. The read and BCD
encode process takes the D.V.M.'s appr9ximately 2 ms. At this time they
generate a print command to the coupler, which senses if it should print,
record, or print and record. In the PRINT ONLY mode it commands the printer
to print. The printer then starts printing and simultaneously holds off the
data coupler. All thirteen BCD characters are simultaneously printed in
parallel across one printer line. This process takes approximately 52 ms after
which the printer releases the coupler which in turn enables another data con-
trol pulse and the counter. The D.V.M.'s will however hold their previous
value until commanded by the next data control pulse to read. The RECORD ONLY
mode is selected by the switch on the coupler front panel and allows the coupler
to command magnetic tape recording. This mode requires a different scanning
and output format. Only one BCD character can be recorded on tape per byte.
The coupler must then command and increment the tape deck thirteen (13) times
for each data word. Again the data control pulse initiates the data record
sequence. The coupler generates read commands to the D.V.M's and holds the
counter. A print return command upon completion of digitization by the D.V.M.'s
activates a clock in the data coupler. The clock pulses sequentially cause
a record and increment of the digital tape recorder. After completion of the
recording of the thirteen bytes the coupler again enables a data control pulse
and the bi-directional counter. The RECORD ONLY data output sequence takes
26 ms and is therefore approximately twice as fast as the print only mode.
The RECORD ONLY mode has one distinctive feature not incorporated into the
PRINT or PRINT AND RECORD modes. Should a data control pulse occur during the
RECORD ONLY mode it is ignored; if a data control pulse occurs during the other
data recording modes the coupler hold may, on occasion, cause a system halt.
The system halt is removed by pressing the reset button on the coupler front
panel. Data recording then restarts with the intervening data missing. The
RECORD ONLY mode ignores this halt so that maximum possible data may be ob-
tained at the fastest recording speed even if requested resolution elements
must be ignored.
The PRINT AND RECORD mode is a combination of the two separate modes. V/hen
the coupler function switch is set to PRINT AND RECORD a data control pulse
initiates the print sequence and record cycle. The counter and data control
enable are inhibited until completion of the record cycle. The time required
by this sequence is the larger time interval of the individual operations (i.e.-
52ms). Data recording can be manually commanded by pressing the "start" button
on the coupler which then makes a single data record cycle. The "Write Error"
indicator lamp on the coupler indicates a parity error and can be removed by
the reset command. The "Tape Not Readinc" lamp indicates the tape is not
properly loaded.
3-130
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3.6.6 Data Recording Subsystem
As was previously indicated there are three (3) data recorders. The strip chart
is an H.P. Model 7701A with a Model 8801A low gain D.C. preamplifier. It serves
as the only analog recording device. Digital data recording is done on an H.P.
Model 5050B line printer and on a Kennedy Model l600H incremental digital tape
recorder. Each of these recorders were incorporated to give the instrument a
particular capability. These capabilities and the various recorder limitations
are described below while detailed specifications are covered in the specifica-
tions section, the electronic details section and in the respective recorder
manuals.
Strip Chart Recorder
The strip chart recorder provides a visual real-time display of system operation.
It is a very useful tool in system set-up and evaluation procedures. The re-
corder will display the source (I), reference (Io) or (T) as selected by the
recorder input switch located on the monochromator control panel. This display
can be used during instrument set-up to find and identify known structure in the
atmosphere. Prior to an actual data scan a rapid scan displayed on the strip
chart can be used to adjust the gain of the system for maximum output without
exceeding full scale. The strip chart display is also the ideal instrument on
which to display system drift and noise. With the monochromator fixed in wave-
number the output is displayed on the strip chart giving a record of long term
stability and noise. There are a number of limitations associated with the strip
chart. All of these limitations concern the difficulties associated with ob-
taining analytical data from this instrument. No wavenumber information is
printed on the strip chart, so wavenumber must be recorded by means of an event
marker at the side of the chart and interpolated as required. Alternately,
specific structure may be recognized and a linear interpolation used to deter-
mine the wavenumber at a point on the graph. Both of these procedures are slow,
tedious and the accuracy is less than desirable. The wavenumber accuracy
obtained by the interpolation is dependent on the chart drive speed and drive
linearity. The amplitude of the signal as read off the strip chart will also
have associated errors. These errors consist of chart readability limitations,
recorder linearity, recorder frequency response and generally the ratio module
accuracy. Chart readability is ± £ division in 50 or ± %%. Chart linearity
at the extremes is also ± ^$. The frequency response of the recorder is down -
no more than 3 db at 30 Hz. This implies but does not specify a flat response
to the 30 Hz corner frequency. Assuming a flat response to 30 Hz allows this
factor to be discounted until the scan speed exceeds 3 resolution elements per
second. This is approximately equivalent to scanning a spectral region in four
(k minutes. The ratio module accuracy is ± 1% above 10$ of full scale (less accu-
rate below 10$ of full scale). The total strip chart amplitude accuracy is
therefore ± 1% for source or reference inputs and ± 2% for (T) input under ideal
conditions. Ideal conditions are near mid-scale display and instrument in a
slow scan mode.
3-131
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Digital Printer
The digital printer serves as a visual real-time display of the digital output.
It prints thirteen characters in parallel at a maximum rate of twenty lines
per second. The thirteen characters are divided into two groups of four, and
one group of five decimal characters. Each character represents a window in a
D.V.M. or the counter. The left most group of characters are the sample and
hold D.V.M. (I) the middle group the ratio D.V.M. (T), and the righthand group
of five the counter (0.1 cm"1). This is illustrated in the table below:
07^76
07^75
07^73
07^73
07^71
07^69
07^67
07^65
07^63
O.lcm'1
The printer reproduces the windows exactly so the only errors are the instru-
ment error and data conversion error. The limitation of this display unit are
the record form and speed capability. The record produced by the printer may
contain a maximum length of 6900 lines when the instrument is operated in the
7-13.5 micron region at O.lcm"1 resolution. The speed capability is 20 lines per
second but at this speed some skipping may occur. At the fastest scan speed with
high resolution data control (o.l cm" ) the speed is limited to about 10 lines
per second. This means that at O.lcm"-1- resolution element scan of the 7-13- 5 p.
region requires a minimum of 12 minutes. Use of the printer in the system
reduces the maximum scan rate and if this rate is exceeded the system will skip.
If higher data rates are desired without skipping the digital output must be
recorded on the digital tape recorder only.
3-132
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Digital Recorder
The digital tape recorder is a Kennedy Madel l600H. It uses a 7 track tape
with byte density equal to 556 BPI and write speed of 0-500 characters per
second. The thirteen data characters are recorded sequentially thus requir-
ing thirteen write cycles to record one data set. The data is formatted on
the tape in a modified BCD code. The advantages of the digital tape as an
output device are its speed and computer compatibility. The cycle time for
the digital recording is 25 ms or forty data sets per second. This is about
four times as fast as the other output devices. The digital tape recorder will
accept O.lcm^resolution elements in the 7-13.5 micron region with scan time as
low as 2^ minutes. The computer compatibility of this output enables a pro-
cedure to generate the other two output formats. Plotting and tabulating
routines have been applied to the digital data as recorded on tape to generate
analog plots and data tabulations of superior quality. The digital tape out-
put is also the simplest method to input to the computer for computational
work. The disadvantages of the digital tape are; no real-time confirmation of
data quality, and the modified data format requires an intermediate reformat-
ting procedure. The digital tape recorder has no playback capability and ^
therefore it cannot be demonstrated that the system is operating properly in
the field. Some reassurance of proper operations given by the write error
and tape not ready indicators on the data coupler. The seven track tape has
tracks designated 1, 2, U, 8, A, B, C, and a convention has been established
for the recording of BCD information on this type of tape. The conventional
code format allows for the recording of numerics 0 through 9, all the alpha
numerics and some other symbols. For the ROSE system only the numerics zero (0)
through nine (9) have significance, and only the 1, 2, U, 8 tracks are required.
Tracks A and B are used as flags while C is the parity bit in this system. A
logic "1" in the A and B tracks is used to signify a new data set. A logic
"1" in the B track is used to signify the first digit of a new instrument.
Hence, every thirteenth byte has A andTJ equal to "l". B is "l" on bytes 1,
5, and 9, as illustrated below assuming the following readings:
Sample-Hold DVM Ratio DVM Counter
00.123 OU.567 89876
3-133
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REPRESENTED DIGIT 1 2 k 8 A B C VALUE OF DIGIT
.0
S-H DVM 10
lo-1
ID'2
ID'3
Ratio DVM 10°
lo-1
" " io-2
10-3
Counter IO1*
n ii 3
io-j
IO2
IO1
10°
0
1
0
1
0
1
0
1
0
1
0
1
0
1
0
1
1
0
0
1
1
0
0
0
1
1
0
0
0
0
1
1
1
1
0
0
0
1
1
1
0
0
0
0
0
0
0
1
1
1
0
0
1
0
0
0
0
0
0
0
0
0
0
0
0
1
0
0
0
1
0
0
0
1
0
0
0
0
0
1
1
0
0
0
0
1
0
0
1
1
0
0
1
2
3
4
5
6
7
8
9
8
7
6
S-H DVM 10U 1010
0
These flags are used by the computer to count the total number of data
sets in a block of data. This is necessary because the total number of bytes
in a block may exceed the computer input capacity. The flag bits are counted
and if they exceed the computer input capacity the tape is copied with the in-
sertion of end of record EOR gaps. Gaps are not inserted during a data run be-
cause the time required to gap would cause the recorder to exclude up to 20 data
sets. This deviation from standard format requires a computer input routine so
that the insertion of the "I's" in A and B are not interpreted as alpha numberic
information. This can be done on the computer or the tape may be copied and re-
stored to a standard format in the support data station.
-------
3»6.7 Electronics Calibration
Electronics calibration consists of an amplitude check of the amplifiers and
data acquisition subsystem. The placement of the operate-standard signal
switch in the STD SIGNAL position inserts a signal of known amplitude into
the instrument just after the preamplifier. The standard signal (T) potentio-
meter on the control panel enables this signal to have any ratio of (I) to
(I0) desired by changing the value of the standard source signal. The standard
signal may then be sequentially monitored in each amplifier chain and the
anticipated values of (I), (I ), and (T) checked on the data recorders.
o
Standard Signal Generation
The standard signal is produced by a circuit called the calibration signal
generator which is located in the logic box. The circuit consists of two amp-
lifiers, one for the source and one for the reference standard signal. Each
is driven into saturation by its respective synch signal amplifier. These
saturated outputs are clipped by zener diodes producing a known amplitude signal
at each of the two chopper frequencies. The source calibration signal generator
output is connected to the standard signal (T) adjust potentiometer on the
control panel. This potentiometer allows the source standard signal to be any
value from 0 to 100$ of the reference standard signal. (T) is therefore what-
ever value of full scale the (T) adjust potentiometer selects. The value of the
zener clipped signal is 6.2 volts, while a low level signal is needed, to simu-
late the preamplifier output. Therefore, the two clipped signals are divided down
to ±6.2 mv or 12.k mv(pp) and combined in the standard signal mixer. This
resistive divider-mixer provides as its output a signal representative of that
present at the output of the preamplifier in the operate mode. When the standard
signal-operate switch is in the STD. SIGNAL position the calibration signal is
inserted into the amplifier chains.
3.6.8 Power Subsystem
The only input power required by the ROSE instrument is 115 volt 60 Hz. Internal
to the instrument power is required in three indirect formsj chopper drive,
blackbody heater and D.C. voltages. The conversion of the 115 volt 60 Hz input
power to the power requirements of the instrument is explained under these
three headings.
D.C. Voltages
The required D.C. voltages are +2^, ±15, ±6, and +5 volts. The +2k volts D.C.
ic provided by the PAR. NIM BIN Model 200. Its primary purpose is to serve
•\a the power supply for the PAR amplifiers. The excess current capability of
3-135
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this power supply is utilized by other circuits; HgrGe detector bias current,
marker selector and source synch prearap. supply voltages are provided by the +2U
volts D.C. supply. A Data Technology Model 597 modular power supply pro-
vides the ± 15 volts and + 5 volts. ± 15 volts D.C. are required by the various
linear integrated circuits utilized in the signal and synch amplifiers. The
total required ± 15 volt power is about 25$ of the rated 100 ma of the 597
nodular supply. Digital logic circuitry requires +5 volts D.C. and the 597
+5 volt output fills this requirement. Total current required by the logic
contained in the logic box is 770 ma, which is less than the 1 Ampere cap-
ability of the 597 module. A ± 6 volts D.C. requirement is generated by the
incremental shaft encoder. Some supply voltage was also required by the LED
used to generate the reference synch signal, and here the +6 volts D.C. is also
used. The total current requirements are 500 ma at +6 VDC'and ^5 ma at -6 VDC.
The two 6 volts supplies are similar, and are located on printed circuit cards
in the logic box. A transformer with a 115 VAC primary and two 12 VAC
secondaries which are rectified is used to generate ± 10 VDC. The ± 10 VDC is
regulated to ± 6 VDC by two integrated circuit regulators. The output of the
regulators drive a transistor to provide the current capability required.
Chopper Drive
Two blackbodies exist in the system; each is chopped by a mechanical chopper
which is motor driven. The source chopper motor is a variable speed D.C. motor,
while the reference chopper notor is a A.C. synchronous motor having a nominally
fixed speed. Thus, two different methods are used to drive the motors. The
reference chopper is fixed in frequency and a synchronous motor is used because
this yields the greatest frequency stability. Frequency stability is imperative
when the signal generated will be amplified in a narrow band system which is
the case in this system. The reference chopper motor requires 115 volts, UOO Hz,
kO watts for nominal operation, which its frequency may be adjusted ± 10
-------
The source chopper is driven by a D.C. motor which sacrifices the inherent
stability of A.C. synchronous motors for variable speed control. Source
chopper frequency in this system is variable from 30 to 3000 Hz. This design
feature is incorporated for the purpose of potentially using the instrument
for a study of atmospheric scintillation effects versus chopper frequency.
An Electro-Optical Industries Model 311 Modulator is the equipment used as the
source chopper. A sophisticated closed loop servo technique provides stability
of 0.25$ which is quite good for D.C. motors and adequate for this system,
Blackbody Heaters
Each of the two blackbodies used in the system has a Electro-Optical Industries
MDdel 216A temperature controller associated with it. The purpose of the con-
troller is to provide a heating current to the resistive heaters located in
the cavity. Heating current is proportional to the difference between cavity
temperature and the temperature set point selected on the controller panel. A
radiometric probe (silicon cell) located in front of the cavity is used as the
sensing element. The probe output is a D.C. signal which is a function of tem-
perature, which, is differentially amplified against a D.C. voltage also a
function of the temperature setting. The differential output is further amplified
and used to drive a power amplifier which has the cavity heater as its load.
3-137
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COMPONENT DETAILS
In contrast to the last section which described system considerations and
component interrelationships, this section provides details of individual
components. Again, there are three main sections: optical, mechanical
and electrical components. A given component may appear in more than one
section. For example, the detector is principally an optical device and
some of the description of the detector is in the optical section. Detector
mounting details are given in the mechanical section, however, and biasing
details, etc., are given in the electrical section.
Wiring tables in Section 8.0 are the prime source of information for
electrical connections and the figures given are intended to augment these
tables.
Except for electrical interconnections the drawings are the prime
source of detailed information and the figures given are again intended to
augment these drawings. Reduced size reproductions of the drawings are in-
cluded in Section 9.0 of this report.
*t.l Optical Components
The components which are primarily optical in nature are the blackbodies,
telescopes, reference optical system, monochromator, detector optical system
detector and synch receivers. For the most part optical component details
are given in this section; there are exceptions and, in these cases, reference
is made to the appropriate section of this report.
k,l.l Blackbodies
The source and receiver blackbodies subsystems are nominally identical units
built by Electro Optical Industries of Santa Barbara, California. The optical
details of the blackbodies have already been described in Section 3.U.I in
connection with the relation of the blackbody cavity to the beam boundaries.
Mechanical details of the blackbody housing geometry and plumbing are
given in Section U.2.U. Operational procedure is given in Section 5.1.1.
-------
Numerous blackbody heater failures have occurred during construction of
the ROSE system. The manufacturer states that the cavity heaters have been
modified to give a reasonable life, ca. 700 hours or so.
After each return from the manufacturer the blackbody settings are de-
termined for a temperature of about l800°K. This is done by means of an
optical pynometer (L&N Model 8622-C) which is calibrated to standards trace-
able to the National Bureau of Standards. The accuracy of the instrument is
believed to be about ± 10 degrees C and the precision of measurement is
estimated (from the mean deviation of about ±1.3 C of the difference between
readings approaching the point of brightness balance from above and below) to
be 3a ~ ± 6 degrees C.
Since there is a temperature gradient across the cavity particularly
along the length of the opening, the center temperature is usually monitored
during warm-up conducted according to the manufacturers instructions. After
the center temperature has stabilized, readings are made at five locations by
means of a small hole placed in front of the cavityj otherwise balance is
difficult to judge. Two readings are made at the cavity ends; one at each
end of the cavity with the hole approximately tangent to the cavity opening.
One reading is made at the center and two intermediate readings are made;
one about halfway between the center and each end. It is important to place
the pyrometer squarely in front of the cavity.
Data taken for one such test are shown on Figure ^..1.1.1 during warm-up.
From the semilog plot it is estimated that the warm-up time to the point
where the temperature difference from the final temperature equals the varia-
tions in final temperature is about 90 minutes.
The spatial profiles of temperature along the length of the cavity opening
for a typical test are shown on Figure U.I.1.2. The spatial variation after
the last rework of the reference blackbody is much less than that shown here
(because a different winding procedure was used, according to the manufacturer).
Since operationally the entire cavity is not used the average of the three
central readings is taken to be representative of the cavity temperature.
Settings are adjusted so that these average temperatures are nearly equal for
the source (S/N 155) and receiver (S/N 15^) blackbodies. Usually this can be
done with one or two trial settings to within the precision of the temperature
measurements. Because of the time required for temperature stabilization this
procedure usually requires one long day.
U-2
-------
Centerline
Temp. -
Tavg (Last U Hrs)
S/N 151* 15^7° C
S/N 155 15^6°C
S/N155(Source )
0.562" Aperture
Turn on at 8:00 A.M.
Full Power at 9:U5A.M.
1U80
12 13
Time of Day-Hours
100
o o o
Mean Dev 1.3°
2 3
Hours After Full Power
Figure U.1.1.1. KLackbody Warmup History
-------
Top
10/8/71
Position Center -
Bot
1U60
S/N 155
(Source)
15^0
Top r
Position Center -
Bot
11460
15^0
(Reference)
Figure U.I.1.2. Blackbody Temperature Profile
U-U
-------
U.I.2 Telescopes
The source and receiver telescopes are nominally identical Model 700 units
made by, Perkin Elmer, Costa Mesa, California. Each telescope consists of
a concave ellipsoidal primary mirror with a central hole and a smaller
convex spherical secondary mirror. This combination is commonly referred
to as a Dall-Kirkham system. The basis for selecting this system is given
in Section 3.U.2.
Figure U.I.2.1 gives a reduced size reproduction of the manufacturers
optical diagram of the telescope.
The optical specifications for the f/5 120 inch focal length Ball Kirkham
telescopes are:
Flat Ob.lect Plane
Total field of view
Distance
Primary Mirror
Diameter =
Axial radius of curvature =
Central obscuration =
Axial separation (to sec.) =
Conic constant (elliptical) =
Secondary Mirror
Diameter =
Axial radius of curvature =
Axial separation (to image) =
. Conic constant (spherical) =
Flat Image Plane
Maximum.distance from axis =
Distance (from pri vertex)
0.25 degrees
Infinity
2k inches
96.0 inches
9.5 inches
30.0 inches
-0.559
9-5 inches
60.0 inches
U-5.0 inches
0
0.2512 inches
15.0 inches
U-5
-------
Figure U.I.2.1 Telescope Optical Diagram
-------
Mechanical details of the telescopes are given in Section U.2.5.
The theoretical optical performance has been calculated for one tele-
scope (as used in the emission mode of operation) which is called the Dall-
Kirkham System and for two telescopes facing each other (as used in the
transmission mode of operation)'which is called the Telescope System. The
results of these calculations using the POSD program are shown on Figure
U.I.2.2 for the Dall-Kirkham System and Figure U.I.2.3 for the Telescope
System. These figures show spot diagrams at the focus of the receiving
telescope in each case. (Corresponding to the monochromator entrance slit
location.)
For the Dall-Kirkham System only two fractional object heights were used,
OBJH = 0 and 1.0, i.e., at the center and the edge of the field of view
(9U rays). The theoretical image height from the axis was 0.251 inches
(or 6.38 mm) which corresponds to OBJH = 1.0 or a half field angle from the
optical axis of 0.12°.
It is necessary to show the spot diagrams on two scales to relate the
spot size to the entrance slit size and still show spot detail. The image at
the edge of the field of view is comatic and 90% of the energy lies within
a radius of about 69 microns (or 138 micron spot diameter). The on-axis
spot size is about 8 micron radius (or 16 micron diameter).
Further investigations were not made since the performance of the tele-
scope in combination with the other system optical components is more
important. (e.g., see Figure 3.^.5.6)
For the Telescope System (at O.U km range) calculations were made for object
heights, OBJH = 0 to 1.0 with U8 rays each. The theoretical image height was
U.6U5 mm which equals hQ/2 for the O.U km range. In addition to the spot
diagrams, a relative irradiance distribution based on the fraction of the
number of rays passing through the system is also shown. This distribution
is a result of vignetting and the results are similar to those obtained in
a different manner, see Figure 3.3.2.6.
The telescopes were tested to determine the axial position of the image
and the focal spot size within which 90% of the energy is enclosed. A distance
of the focal spot from the telecope mounting plane was specified to be
12.00 ± .03 inches. The focal spot diameter was specified as 150 microns.
«*-7
-------
100 Microns
H
100 Microns
I -
Rad.= 69 p.
Dia.=138 V-
OBJH =1.0
Rad.~ 8 M-
Dia 16 \i
OBJH = 0
Magnified spot diagrams at
focus of Dall-Kirkham Astern
(i.e. at the monochromator
entrance slit). Scale 1 in.= 0.1 mm
Cross is actual chief ray position.
Dot is theo. image location.
•Entrance Slit
0.3 x 12.0 mm
Figure U.I.2.2 Ball - Kirkham System Performance
-------
100 Microns
OBJH =0.8
+ t
I I I L*m 111
Til1 r*"1
0.5
0.2
100 Microns
Scale: 1 in. =0.1
OBJH =0.1
mm
Entrance Slit
X 0-3 ^ 12.0 mm
Magnified spot diagrams at
focus of Telescope System.
Cross is actual chief ray position.
Dot is theoretical image location.
1.0
elative Irradiance
-5 -
Image Boundary
Range = O.U Km
Figure '+.1.2.3 Telescope System Performance
-------
During the tests the telescopes were supported on test stands which
support the telescope in the same manner as it is supported in operation.
The axial position of the image was determined by use of a test tool which
is threaded to screw on to the rear of the primary mirror mount. A cross
line reticle on the test tool is adjusted to be 12.00 inches from the tele-
scope mounting plane. The axial position of the focal spot for a well
collimiated beam (see below) was determined by comparison with the reticle
position by means of a microscope to which a dial indicator (reading axial
distances) was attached. Both the test stand and the test tool described
above are being snipped along with the ROSE system.
A telescope test source using an available 2k inch diameter, 152.6 inch
focal length parabolic mirror, a 2k inch diameter flat mirror and flat dia-
gonal mirror was set up as shown in Figure k.1.2.**. The parabolic mirror
axis was found by means of a laser and the diagonal mirror; the laser was
pointed at the center of the parabolic mirror (with the beamsplitter assembly
removed) and the laser and diagonal adjusted so that the going and return
spots were aligned at both the laser and the diagonal. The 6? micron hole,
mounted in the exact center of a hole in a precision square block,was aligned
with the laser beam and was fully illuminated by a microscope objective with
a uniformly illuminated ground glass at its long conjugate. The beamsplitter
assembly was moved along the axis until the image reflected by the beamsplitter
and observed by means of a microscope was at the face of the precision block.
This places the pinhole on the axis at the focal point of the parabolic mirror
and results in a precisely collimated beam from the parabolic mirror to the
flat mirror.
The effective source size of the source system was evaluated using a
photometer at the return focus of the system shown on Figure 4. 1.2.1*. The
photometer was made up from available equipment consisting of a Gaertner
miscroscope (32 mm objective and a 10X eyepiece in a filar micrometer), a
photographic lens (Zeiss Biotar 58 mm f/2 to f/l6), and a photomultiplier
(RCA 7265). The microscope eyepiece projects the test image on the diaphragm
of the Biotar lens. The exit pupil of the test object is focused on the
photomultiplier. By changing the Biotar diaphragm the size of the image from
•which energy is received may be controlled. An arbitary scale was attached to
the diaphragm control and was calibrated by measuring the image of the diaphragm
at the telescope image plane using an auxiliary micrometer microscope. For
this calibration a diffuse source was placed in the location normally occupied
by the photomultiplier. Focus was obtained with both the filar cross hairs
and diaphragm edges in focus. The calibrated image size range was from 7^
to 66k microns.
k-10
-------
Flat Mirror
2U" Dia.
Pellicle
Beamsplitter
Flat Diagonal
-Microscope or
Photometer
Laser
Precision
X-Y Table
Parabolic
Mirror
2U" Dia. 152.6 F.L.
Figure U.1.2.U Telescope Test Source
-------
A chopper was installed between the light source and the pinhole, and
photometer readings were taken on a Princeton HR8 lock-in amplifier for various
diaphragm settings after first centering the photometer for maximum signal with
the smallest aperture. The energy with the wide open aperture was taken as 100$.
from the resulting curve of output versus image size the image size for 90$
energy was obtained. The correction to be applied later to the telescope
image size observations for the finite source size and collimator imperfection
was evaluated by taking photometer readings on the image reflected by the pellicle
in autocollimation. It was found that the parabolic mirror had a turned edge and
was not precisely parabolic although the figure was smooth. Measurements at the
full aperture of 24 inches and at 20 inches gave 90$ energy spot sizes of 380
and 270 microns, respectively in autocollimation. It can be shown that in
autocollimation a slope defect produces double the displacement of a single
reflection. Thus for the telescope focal length of 120 inch the 90$ energy
size of the source is (380/2) (120/152) = 150 microns for a 2k inch aperture and
(2?0/2)(120/152) = 107 microns for a 20 inch aperture.
The telescope test source (consisting of the parabolic and diagonal mirrors,
the 6? micron pinhole and the light source) was used to evaluate the telescope
image as shown in Figure U.I.2.5. The laser was first set up (with the telescope
removed) on the axis of the parabolic mirror behind the telescope position by
making the spot returned from the center of the parabolic mirror coincide with
the laser source. The telescope mounted on the test stand was then placed in
position so that the laser beam was centered on the crossed wires at the center
the telescope field mask. (The field mask center was used by Perkin Elmer in
their alignment). The test tool was attached to the threaded primary mirror
mount in which the field mask is mounted. The threads and field mask are con-
centric. A reticle on this tool was placed on the thread axis by adjusting the
reticle laterially on the tool until no motion was observed with the microscope
when the tool was rotated on the telescope threads. The reticle was then placed
at the specified distance behind the mounting plane. The telescope axis is now
defined by the reticle and crossed wires at the center of the field mask. The
telescope was aligned to the collimated beam by placing the center of the field
mask (defined by the crossed wires) on the laser beam and rotating the telescope
until the telescope image fell on the reticle cross lines.
The telescope image was evaluated by placing the photometer behind the tele-
scope focus and aliening it as described before. Image evaluations were made
on the axis and at the edge of the specified ± 0.125 degree field of view which
corresponds to about ±0.25 inch at the telescope focus.
The results of the photometer tests are as follows:
U-12
-------
Laser
Microscope or
Photometer
Reticle at
Telescope focus
Telescope
Field Mask
Light Source and
Diagonal
Parabolic Mirror
Figure U.l.2.5 Telescope Test Set - Up
U-13
-------
Location
i"
On Axis
" Down
Parab. Aper.
2U"
20
20
2U
Telescope #2
i" UP
On Axis
Down
20
2V
20
2k
20
2U
20
Obs.
Image Eff. Source
150 Microns
107
290 Microns
235
280 150
225 107
285 150
2U7 107
280 150
270 107
280 150
230 107
312 150
310 107
Microns
128
130
118
135
130
163
130
123
162
203
Image Size Axial Pos
11.96 in.
11-97
11-97
12.00 in.
12.00
12.03
The average difference in 90# image size for the 20 and 2U" apertures for
telescope #1 was 10 microns and for telescope #2 was 27 microns.
,In view of the magnitude of the effective source size and the uncertainty
of these values it is considered that both telescopes are acceptable for
image quality (even though telescope #2 at the £" down position may slightly
exceed the specification values of 150 microns).
-------
U.I.3 Reference Optics
The reference optical system (except for the blackbody and the toroid) was
built by Convair and is described on drawing 596-722-010. The optical comp-
onents for the reference optical system are shown on drawing 596-722-007.
The system provides a reference beam for the system as described in Section S-
There are three glass mirrors in the reference optics system plus the
chopper which also has a mirror surface on the side nearest the monochromator
(see figure U.I.3.1). Each surface is aluminized with a quarter-wave (visible)
protective coating of SiO.
The reference beam starts at the reference blackbody. One conjugate
focus of the spherical mirror is located at the middle of the front plate of
the blackbody outer housing, the other conjugate focus (at unity magnification)
is located at the intermediate focus. The beam is turned by means of the flat
diagonal mirror between the spherical mirror and the intermediate focus. A
toroidal mirror (60 degrees off-axis) is used to transfer the bean from the
intermediate focus to the entrance slit» The chopper inclined at about 4 5
degrees serves to turn as well as chop the reference beam.
As indicated in the optical diagram all of the elements of the reference
optical system are sized so as not to limit the reference beam. The apertures
are the entrance slit and the mask on the grating in the monochromator.
The reference chopper is considered part of the reference optical system.
The 30U stainless steel blade was made from a blank gear. The blades were
milled on one set-up after which the blade was polished using stainless steel
inserts to fill the gaps between the blades. Finally, it was aluminized and
overcoated with SiO.
U-15
-------
Ref.
BLackbody
P.L.
Sphere
Intermediate
Focus
125fflni F. L.
60° Off Axis
Toroid
Entr.
Slit
Pupil
2l*.8mm
dia.
12 nm
High
Entrance
Slit
Toroid
Sphere
Refere nee
Blackbody
Flat
Diagonal
Figure k.1.3.1 Reference Optics Diagram
U-16
-------
U.I.U Monochroma tor
The monochromator is a Model 210B made by Perkin Elmer, Norwalk, Conn, with
a number of modifications made by Convair. This section will be devoted
mainly to the modifications. An optical diagram of the monochroroater is
shown on Figure 3-UA.l which is the best estimate of its configuration since
an optical layout was not available from the manufacturer.
Mechanical details of the monochromator mounting and mechanical modifications
are described in Section k.2.7.
The monochroraator is an off-axis Littrow design using two interchangeable
gratings. The grating data taken from the labels on the back of the grating
is as follows:
Part No. 032-1006 Serial No. 01-1-6-G
21*0 grooves/mm ELaze Frequency
Blaze Angle 20° Blaze Wavelength 3^00 cm"1 *
Blaze -*
* obviously in wrong place (1/31+00 = 2.9^1 microns)
Part No. 032-1005 Serial Ho. 02-11-8-F
101 grooves/ram Blaze Frequency
Blaze angle 22°-2' Blaze Wavelength 7.5 microns
Blaze -»
Access to the grating change control is obtained by removing the round
cover on top of the monochromator; the grating control is spring loaded in the
up position. Pushing down on the control allows engagement of a pin on the
grating mount. Then, by turning the control gently the grating mount can be rotated
to place the desired grating in position. The contact at the end of the
rotation is by means of a magnet on the grating mount which positions the
grating precisely against stops at each end of the rotational range of travel.
There are two long wave pass filters provided, one for use with each
grating. Curves of the transmission of these filters are given in Figure U.'l.U.l.
The filter may be changed by means of a knob on top of the monochroraator.
Four positions are plainly labelled: open, 3-5.5 micron, 7-13.5 micron, shut.
One optical modification of the monochromator has already been discussed
in Section 3.k.h}namely the removal of a mask on the collimating paraboloid.
It restricted the available aperture and,as shown in Section 3. I*.U, was not
necessary in the present case.
U-l?
-------
9 10 11
Wavelength - Microns
0
1* 5 6
Wavelength - Microns
Figure U.I.U.I Filter Transmission
U-18
-------
Another modification described in Section 3.U.U, is the addition of a mask on
the grating which serves as one of the apertures of the system. An outline
of the mask is shown in Figure U.1.U.2 below. The nominal mask open area is
P 2
15.9 cm ; The measured mask open area 15.1 cm for the 101 L/mm grating mask
and 15.7 cm for the 2^0 L/mm grating mask.
Figure k. 1.U.2 Grating Mask
Because of the large range of image size on the entrance slit it was
necessary to add a slit height adjustment mechanism.
Since the space available close to the entrance slit is very limited a
custom designed assembly was required. Figure U.1.U.3 shows this mechanism
schematically; for more details see drawing 596-722-012. Although this is a
mechanical device its major function is optical and, therefore, will be des-
cribed here. A parallelogram is actuated by a micrometer screw through a 2:1
ratio lever. The result is a bilateral opening slit whose width is nominally
equal to micrometer reading if the zero's are properly set. Note that (in
order to obtain direct reading) the micrometer closes the slit which is opposite
normal practice; to prevent jamming the slit jaws, a stop was provided on the
micrometer screw. Nevertheless, excessive torque on the micrometer should be
avoided.
To prevent possible problems from sticking it is preferable to set this mic-
rometer with a decreasing reading.
A hole in the monochromator cover permits convenient access to the slit
height micrometer control. Care should be exercised in removing and replacing
the cover not to place undue force on the micrometer.
-------
Micrometer
0-13mm
Figure 4.1.U.3 Slit Height Assembly Schematic
U-.20
-------
A field lens made of Irtran 2 (uncoated) was added (Just ahead of the slit
height adjustment assembly) which images the grating mask on to the telescope
exitpiwll. Since this pupil is the image of the telescope primary mirror
formed by the telescope secondary mirror the grating mask is thereby imaged
onto the telescope primary mirror. The grating mask image is the ^iver
telescope entrance pupil. The entrance slit of the monochromator defines the
field of view of the receiver telescope.
No theoretical optical performance calculations were made for the mono-
chromator alone. However, Figure 3.U.5-8 shows that addition of the mono-
chromator had little effect on the Dall-Kirkham system optical performance
with the Detector "Cassegrain". Consequently, the monochromator aberration
contribution to the system is considered to be small relative to those of
other components.
The entrance and exit slit jaw width was checked against the slit micrometer
drum setting. A Gaertner microscope slide having 10 micron drumdivisions with
r32 mm objective and a 10X eyepiece (overall ~ UOX) was used. The correction
is defined as the slit width minus the setting. The maximum correction was
8 microns and the minimum correction was -13 microns for the exit slit. The
mean correction for the exit slit was -3.6 micron (k.k micron without regard
for sign). For the entrance slit the maximum correction was U* microns and
the minimum correction was -7 microns; the mean correction was +1.9 microns
(U.6 microns without regard for sign). The precision of setting on an edge was
about ±1.5 microns so that the precision of a slit width measurements was about
\ to 3 microns. Thus, the corrections are not much more than would be exp cted
from a normal error distribution and it is therefore recommended that corrections
for the slit width be neglected. If more precise widths are required, meas-
urements of the slit width should be made.
The slit height assembly was calibrated several times and as noted above,
it was found best to set the micrometer with a decreasing reading. The same
microscope as that used for the slit width measurements was used for these
calibrations. The maximum correction was 0.038 mm and the minimum correction
™s 0 002 mm. The average correction was .0.021 mm. For slit heights above
Lut 1 mm the corrections are less than 1* of the slit height. Before
it is considered that the slit height corrections may be neglected under normal
conditions. If more precise values are needed a recalibration should be made.
A number of wavenumber calibrations have been made from time to time. Some
of the earlier calibrations are no longer valid because the monochromator has
been realigned by the manufacturer several times. The last alignment was made
in December, 1970 and all data shown here were taken since that time.
*-21
-------
There are a number of gases which are useful for wavenumber calibrationj
these are shown on Figure ^.l.U.U at the spectral intervals for which each
could be used.
The latest wavenumber calibrations are as follows.
SkO L/mm Grating:
V = 1^72.9 + 123.9 WD cm"
lOlL/mm Grating:
V = 619.9 + 52.2 WD cnf
where WD = no. of wavenumber drum turns
A discussion of set-up of these equations into the system is given in
Section 3.5.2. Deviations from the above equations based on known molecular
lines are given in Figure k.l.h.5.
U-22
-------
3.0 - 5.5M- Band
HBr
3.On
I
~ UOcm
Atm
HC4
~ 20 cm
CO
Acetylene
I* -I
P.W 1.5cm
Atm (L=7m)
P=3cm (L=lm)
Methane
10 cm
Atm (L=7m)
1600
i
rvj
to
1800
13.
I
Acetylene
{• . -I
P=8cra
2000
2200
2UOO
2600
2800
3000
3200
3^00
360
-1
v - cm
7.0 - 13.5u Band
L=7m
P=7-12cm
.Methane
P=12crn
Atm (7m)
Pressures and path lengths
as described by
E. K. Plyler et al,
J. of Res. NBS,
an.
Calibr. Gases
CO
CO (Atm)
•HBr
HCA
C2H2
NH
H20(Atm)
600
800
v - cm
-1
1000 1200 1UOO
Figure U.l.U.U Gases Useful for Wavenumber Calibration
Path = 5 cm unless otherwise noted.
-------
101 L/mm
v= 619.9 + 52.2 WD
5/26/71
15 16 17 1800 i
\>-cm
Laser Calibr v = 567-9 + 52.^ WD
1/2U/71
L/mm
v = Itt72.9 +123-9
5/19/71
0
-1
-2
-3L
Laser Calibr. v= 13^7.3
1/23/71
v= actual wavenumber
v. = indicated wavenumber
\
\
\
Figure U.2.U.5 Deviations from Wavenumber Linearity
-------
Detector Optics
The detector optical system was designed and built by Convair and is described
on drawing 596-722-011. The optical components for the detector optical system
are shown on drawing 596-722-008. Mechanical details are discussed in Section
U.2.8.
The detector optical system reduces the image at the monochromator exit
slit by a factor of six. A toroid reduces the exit slit image by a factor of
two and the remaining reduction of three is accomplished by the detector
"Cassegrain" see Figure 3.V.5.I. The quotation marks indicate that the system
is not strictly a Cassegrain system since it utilizes spherical surfaces.
Nevertheless, the name is commonly applied to two mirror combinations of this
sort and will be used here for convenience.
The theoretical performance of the detector optical system is most usefully
given in combination with the other system optical components; this has already
been shown in Section 3.^.5.
There are four mirrors in the detector optical system: a toroid, a flat,
a convex secondary and a pierced concave primary mirror. All are aluminized
and overcoated with SiO. In addition an uncoated Irtran 2 field lens is used
to control off-axis rays by imaging the toroid exit pupil onto the "Cassegrain"
center of curvature (the two "Cassegrain" mirrors have a common center of
curvature).
An optical diagram of the detector optical system is shown in Figure ^.1.5.1.
This optical diagram can be used for the optical alignment of the "Cassegrain"
assembly by placing a small image on axis at the field lens surf ace, observing
the image at the detector location and adjusting the Cassegrain ring until the
sharp and symmetrical detector image distance is at the proper location. The
location and size of the pupil just ahead of the .detector is not well defined
because of aberrations. Numerous rays were traced for a variety of conditions
both with the Dall -Kirkham System (one telescope) and Telescope System (two
telescopes). From all of these data it was decided that a detector mask
corresponding to 10.0 mm diameter at 5.0 mm from the detector would be the best
size and location; this gives an approximately 90° field of view at the detector.
-------
12mm High
lOOmmF.L.
20° Off-Axis
Toroid
Front
Surface
Field
Lens
- Detector
Pupil
\_ Detector
"Cassegrain"
See Detail Below
Toroid
Focus
12.70*
mm
(0.500")
*Back of Sec. Mirror
Mount to Focus
(Without Dewar Window)
Figure U.I.5.1 Detector Optics Diagram
-26
-------
U.1.6 Detector
The detector was supplied by Santa Barbara Research Center (SBRC) and is made
of mercury-doped germanium (Hg:Ge). It is described by the following purchase
specification and the specification drawing shown in Figure U.I.6.1 (see also
drawing 596-722-016).
The following specification (along with the Detector Specification drawing
shown in Figure U.I.6.1) was used for detector procurement.
Detector Specification
Type Mercury-doped germanium
Wavelength of Interest: 3.0 to 5.5 and 7.0 to 13.5 microns
Element Size: 0.2 X 2.0 mm (see accompanying drawing)
Field of View: Approximately 90 (10 mm baffle at 5 mm)
Mounting: Copper base with detector attached to
terminalsj mounting may be electrically
insulated from cold finger.
Operating Temperature: 26 K (closed cycle mechanical cooler)
Blackbody D* (90°, 500°K, hOO Hz): £ 1 X 1Q10 cm Hz^/watt
6 U 7
Effective Source Impedance: 10 ohms nominal; 10 to 10 ohms acceptable
Application: Ground based field spectrometer
Chopping Frequency: UOO-2000 Hz
Responsivity: As uniform over the surface as possible
Performance data to be supplied by manufacturer.
-------
NOTES:'
/ ALL D/H. /A
2. DETECTOR TO 6£
.003.
. ; rot. at. 03 tua/ss £ HOTE0.
TV swerve?
3. DETECTOR. S/Z£ - 0. Z* 2.0 MM (o.OOT?* 0.079 M>). -j
4. MOUNT MATZKIAL - COPPER
HERMETIC TYPE
SOLOCttG TO B*S£(2.).
5. AP£KTURE TUS£
TO BASE.
DC MOT SCAL£
GENERAL DYNAMICS
CONVAIR DIVISION
SAN DIEGO, CALIFORNIA
SIZE
CODE IDENT
14170
DRAWING NO.
Flgure u ± 6
'
UJ -i
>-
>-
UJ
_J
Z_
-
\DE TLCJOR SPEC DKWG. .
SCALE
[RELEASED
SHEET
looc
IDISTR IFORM . ----
-------
The detector installation on the detector cryocooler cold finger is
shown on 596-722-016 and is described in Section U.2.9.
The detector was examined carefully both for geometrical and electrical
conformance to the specification; it met them all.
The following table shows the performance as reported by SBRC and as meas-
ured by Convair,
Convair SBRC
Flux density, watt/cm2 (RMS) 0.6U X 10" 1.8 X 10~
Signal, microvolts (Ri-23) 170 , 395
Responsivity(BB). volts/watt 6.6 X 1CT - ,
Responsivity(Xm)i volts/watt 12.0 X KT 9-9 X 10^
Noise, microvolts (RMS) 0.8 O.U4
NEP(BB), watts _ 12.0 X 10'12 7-9 X lO'-1^
D*(500°K,f) cmHzi/watt 5-3 X lo9 8.0 X 10?
Frequency f, Hz 630 l800
D*(\m,f ) cmHzt/watt 0.95 x 1010 1.^5* 1010
Voltage across det.&load volts 23- 20
load resistor 10K 10K
Detector resistance 12 .8K 12. 6K
Detector current, ma 1.01 0.885
Thermal noise of a 10K precision 1% resistor (with the 10K load resistor)
measured 30 x 10~9 volts (RMS); this corresponds to a calculated thermal
noise of 22 x 10~9 volts plus preamplifier noise of 20 x 10~9 volts (calc.
N.F. - 2.7 db) for a total of 30 x 10~9 volts (RMS). The manufacturer
specifies N.F. - U db at a 5K source resistance for 300-600 Hz.
Time and money did not permit detector uniformity tests to be made.
However, from the volumetric nature of the absorption it is estimated that
the responsivity is uniform within 10$ or less.
J4-29
-------
A noise test of the preamplifier was made with a 10K 10$ precision
resistor at the preamplifier input in place of the detector. The pre-
amplifier gain was 1000. The noise at the preamplifier output as
measured by a Hevlett Packard 302 A waveanalyzer (f = 630 Hz ; Af = 6 Hz)
varied from at least 15 uV to occasional peaks of 60 piV with the average
being about 25 to 30 M-V. (No output integrator was used on the wave-
analyzer .)
Taking the thermal noise for the 5K source impedance (lOK resistor in
parallel withkthe 10K bias resistor) equal to v^KTRAf = (U(l. 38*10 J/°C)
(300)(5K)(6))2 = 22 nV rras and the equivalent input noise of (30 u.V/1000)
30 nV rms,
N.F. = 20 lo
[' '""P - — = |^ = 1-36] = 20(.135) = 2.7 db ~ 3
t
The amplifier input noise is about 20 nV rms in the 6 Hz bandwidth or about
8 nV rms/jAz = 0.008 u-V rms/JIz vhich is small compared to the detector
noise (see below).
With the cooled detector (window covered vith aluminum foil) attached to
the preamplifier input, the noise at the preamplifier output was at least
1.5 mV to occasional peaks of i| raV with the average being about 2 mV as
indicated on the waveanalyzer. The noise at the detector was therefore
about (2.0/1000 ~ 2 p,V rms) in a 6 Hz bandwidth or about 0.8 uV rms/v/Hz-
A later test with an integrator on the waveanalyzer output gave the same
result. SBRC report a noise of O.UU u.V rms for a 1 Hz bandwidth. The
difference may be in the cooler since SBRC used liquid He cooling.
The detector noise was also recorded on the analog recorder of the ROSE
system (G = 1000 x 1 x 100 and Q = 10; T = 0.01 sec). A noise of about
M divisions peak to peak was observed at 0.5 V/div = 2 volts peak to peak
or 20 u-V pp at the detector. For a bandwidth of (-^ = ) 25 Hz this corresponds
to about, h u.V_ppA/Hz and with a (peak to peak/rms) factor of about 5 gives
0.8 M.V rms/^Mz. A record at T = 0.1 gave a peak to peak noise of about
1.5 div as expected.
-------
A 500°K blackbody was set up 113 ± 1 cm from the detector to the aperture
plane of the blackbody. A chopper (blade width ~ O.ljl") was placed
betv;een the blackbody and the detector. The detector was connected to the
preamplifier (G = 1000) and its output was read on the waveanalyzer
(f ~ 630 Hz). F/ith a 0.2 inch (= 0.508 cm) diameter aperture the voltage
was 172 mV on the waveanalyzer which is equivalent to 172 u,V at the detector.
The ROSE system was also used to measure the voltage (G = 1000 X 1 x 50)
and read 8.U volts which corresponds to 168 u-V at the detector. Checks of
the voltages obtained with O.U and 0.1 inch diameter apertures agreed
within about % of those expected on the basis of the nominal aperture
area. Checks at preamplifier gains of 100, 200, 500 and 1000 agreed with
those expected from the gain change within about 1%.
An average value of 170 ^V was used to calculate the detector performance.
With a modulation factor of 0.590, the ratio of the rms fundamental flux
to peak to peak flux is 0.590/v^ = O.Ul?.
P = [N(500)-N(300)][(.5082) Y /(113)2](.M7)
S" f)
= (0.113-0.015) (1.58 x I0"5)(.'il7) = 0.6U x 10" watt rms/cm
The blackbody responsivity is
R = 17° X 10 = 6.65 x 10U volts/watt
BB (o.6U x io~6)(.ooU)
The responsivity at the peak is 1.8 times the blackbody responsivity according
to SBRC.
R = 6.65 X 0 (1.8) = 1.2 X 105 volts/watt
The blackbody NEPDT1 = °' * 1?^,- = 1.2 X 10" watt for a 1 Hz bandwidth.
BB b.o~> *
= 1.2 x 10 watt for a 1 1
The blackbody D*(500K5630 Hz) = ^~ = '^ n = 5-3 X 109 cmHz2/watt
"DTI 1 o y "i o *
DD -L * d. A -LVJ _ \^
and the peak D*(X ,630 Hz) = 1.8(5-3 x 109) = 9-5 x 10 cmHz2/watt.
m
Measurements vrere also made of the detector response at various angles of
incidence by rotation of the detector-dewar assembly about axis in the plane
of the detector perpendicular to the length and width of the detector. The^
results are shown on Figure 14.1.6.2. Since it was quite difficult to position
U-31
-------
the dewar assembly precisely, the angles given are probably no more
precise than ± 5 degrees or so.
-------
Rel. Response
1.00
Rel. Response
1.00
cosfl
-50
End of Detector
Nearest Motor Conn.
Figure lj.1.6.2 Detector Off-Axis Response
«»-33
-------
k.1.7 Synch Systems
Two synch systems are required: one for the source beam and one for the
reference beam. Both were designed and built by Convairo The source synch
receiver assembly is shown on drawing 596-722-017 and the reference synch
optical details are shown on 596-722-010 (Sheet 3),
The optical diagram of the source synch receiver is shown on Figure 3,^.7.1.
The objective lens is k$ mm clear aperture and 1^7 mm focal length. The field
lens (used to make the synch receiver alignment less critical) is a ^3X 0.65 NA
microscope lens with the normal short conjugate at the synch detector. The
field lens is shov/n schematically as a simple lens since the exact lens config-
uration is not known, me field lens aperture, however, is approximately 2 HA.
(focal length). For an optical tube length of 160 inra the focal length is approx-
imately 160/43 ~ 3«7 an. Therefore, the field lens aperture is about 1.3 (3.7)~
5 ram diameter. The resulting total field of view of the objective is about
= 0.03^ radians or approximately 2 degrees.
The image of the objective on the detector is about (3. 7/1^7) (^5) ~ 1.1 mm,
the detector diameter is nominally 1.5 mm.
Normally the image on the field lens vd.ll be quite small so that misalign-
ments of about ± 2 mm over the objective focal length in either direction can
be tolerated (compared to about ± 0.5 mm if the field lens were not used).
The etendue of the synch receiver system at a maximum range of ^.0 km is
estimated to be about 2.3 x 10 cm steradian. This corresponds to a source
size in a short range laboratory set-up of about O.017 inch diameter. Satis-
factory source synch operation was verified in the laboratory for source
aperture diameters down to 0.010 inch diameter.
For short ranges (less than about 150 to 200 ft) the off axis location of
the synch receiver makes the use of an auxiliary periscope necessary. Such a
periscope is provided for short ranges particularly in the laboratory.
^.1.8 Alignment Systems
The alignment devices were designed and built by Convair and are intended for
use in aliening the source and receiver stand assemblies. Details of the align
ment devices are shown on drawing 596-722-OlU.
There is a wide-field and a microscope alignment device for use at each
stand assembly. The devices for use with the source stand assembly (which
attach to the source blackbody) are not interchangeable with those for use
with the receiver stand assembly. The latter slide into the clip at the
monochroraator entrance slit.
-------
A reticle is incorporated in each wide-field alignment device. A
central cross 10 mm long is divided into 0.5 mm intervals'. The center is
the aiming point for coarse stand alignment. The short lines of the scale
are 0.3 mm or 300 microns long and the long lines are 0.7 mm or 700 microns
long corresponding to the two slit widths required for the specified spectral
resolution of 0.01 micron for the 101 line/mm and 2^0 line/mm gratings,
respectively. It is intended that these may be used for estimation of the
field view in the emission mode of operation. The remainder of the reticle
field is covered with a grid the lines of which are spaced 1.0 mm apart.
These may be used for range estimation to objects of known size or size
estimation of objects at known range.
The microscope alignment device contains a cross hair the center of which
is the aiming point for precise stand alignment.
R»r further details of alignment device use see the System Operation
Section 5.0.
-------
U.2 Mechanical Components
In this section detailed descriptions are given of components which are
primarily mechanical as well as the mechanical features of other components.
The components which are primarily mechanical are the stands, the auxiliary
stands and the electronic enclosures. These are combined along with other
equipment into a source assembly and a receiver assembly as shown in Figure U.2.1
and general assembly drawing 596-722-003.
The other components whose mechanical features are described here are for
the most part components which primarily serve an optical function.
The approximate size and weights of the major assemblies shown on Figure
U.2.1 are as follows:
W
H
Wt. (est.)
69"
27.5
26
25
69
27.5
29.5"
26.1
22.3
22.3
29.5
21.1
U8.5"
50
53.8
53.8
^7
ko
koo
. 270
370
370
300
210
Iten
Receiver Stand Assembly
Receiver Aux. Stand Assy.
Electronic Console (DVM)
Electronic Console
Source Stand Assy.
Source Aux. Stand Assy.
U.2.1 Stands
The stands were designed and built by Convair and serve as the major supporting
structure for the other components. There are two stands: a source stand and
a receiver stamd. They are nominally identical except for some additions to
the receiver stand. The basic framework is shown in Figure U.2.1.1 and, in
more detail, on drawing 596-722-005. The framework material is aluminum to
minimize thermal alignment variations.
Electrical power to the receiver stand is normally supplied from the elect-
ronic consoles but may be supplied from an independent source if desired. The
only unit in the stand supplied directly from the 110V 60 Hz stand line input
is the mercury lamp and amounts to only about 0.2 amp. Of course, any equipment
plugged into the convenience outlets would add to this load.
The extruded tubular framework elements are one inch square (outside) with
a one-eighth inch wall thickness and are joined together by welding. After
welding and stress relieving the assembly critical areas at the locations of
the. telescope pads and the mounting holes for the monochromator (receiver)
or blackbody (source) were carefully machined. Finally, equipment and trim
-------
•70 SOURCE ASSY.
rftt-nt-MO-** r
I flMCTf»ftC I
^ JLffin
s nf» ***$**—j
-ruifi**?**^
-l&»*
/twDW^wr
-60 RECEIVER ASSY.
Figure lt.2.1 Source and Receiver Assemblies
-------
fff-ltl-OOl
t PLACES C*CH SIDE
ZfLACES (ot/ot/rs/of
or -2?
t nates
Figure U.2.1.1 Stand Assembly
-------
panels were installed as shown on drawing 596-722-006. The stands are painted
EN-2GO gold to match the electronic consoles. Telescope number one is mounted
on stand number one and is us---*, for the receiver assembly. Telescope number
two is mounted on stand number two and is used for the source assembly. All
trim panels are marked on the inside surface for identification (telescopes
are marked on the rear surface of each primary mirror).
The major load on each stand is the telescope which is attached to the stand
at three pad locations. Taper pins are used at each pad to ensure that alignment
will be preserved throughout disassembly and reassembly of the telescope on the
stand. It can be observed from the arrangement of the framework members in
Figure U.2.1.1 that the loads are earn.or" directly to three pads upon which
each stand rests.
htost of the telescope weight is carried directly down to the support pads
by frame members in compression. Since the telescope center of gravity is forward
of the front pads there is an overturning moment which is carried as a couple
by the upper frame members; the resulting loads are again carried directly by
tension or compression to the support pads. The static deflection of the front
of the telescope is about 0.005 inches. Every effort has been made to utilize
tension or compression members and to avoid bending members so as to reduce
structural deflections.
The other major component mounted on the stand is located near the telescope
focus: the monochromator on the receiver stand and the source blackbody on the
source stand. These two components are each mounted in a similar manner by means
of the mounting plates; see drawing 596-722-OOU. The entire mounting plate is
attached to the stand by means of three screws each of which allow vertical
adjustment. Common rotation of these screws results in vertical translation of th;.
mounting plate while differential rotation results in rotation of the plate
about horizontal axes. Cap nuts on top allow the screws to be locked after
adjustments are made.
Lateral positioning or rotation about a vertical axis of the component mounted
is accomplished by three screws which act against spring loaded plungers. Beforo
adjustments are made three bolts which lock the component to the mounting plate
should be looucned (tighten after adjustment). Access to these bolts is obtained
by removal of one side panel of the stand.
Note that these mount adjustments move all of the components relative to the
each telescope. For the source system only the source blackbody is moved. For
the receiver system the monochromator along with the reference optical system and
detector optical system attached to it are moved as a unit. Thus, the rel-
ative alignment of these latter components is not disturbed by repositioning of
the whole unit relative to the telescope focus (except the sphere of the reference
optical system must be readjusted since the reference blackbody position is fixed),
U-39
-------
xne s'taiiu atibemoxy may ue conveniently adjusted, in az-uiiuui auu eo.evuc.ioii.
The stand was designed to pivot about the vertical axis of the rear pad each
front pad being a radial distance of Uo.35 inches from the rear pad. Coarse
azimuth adjustment is made by moving the stand as a whole and fine adjustment
in azimuth over a range of about ±1° is made by means of control knobs on the
front pads (connected by means of a tie rod) which turn a screw mechanism; see
Figure U.2.1.2. Turning the knob on either pad turns a 6k threads per inch
screw which causes the stand to rotate about 0.0156/40.35 ~ 0.00038? radians
per turn or 0.022 deg per turn. At the longest range of 4 km this corresponds
to about 1.5 meters/turn so that the telescope diameter of approximately 0.6
meter corresponds to about 0.4 turn. The corresponding image motion at the
telescope focus (normal to the slit length) is about 1.2 mm per turn. Knob
motion for the image diameter of about 0.93 mm (corresponding to 2 telescope
diameters at k km) is about 0.8 turn. Although a finer screw would give more
precise pointing of the system it was decided that this was the finest practicable
screw that should be used. At shorter ranges the linear range of adjustment
is correspondingly less being about 0.15 meter/turn at 0.4 km; therefore, a
motion equal to the telescope diameter at 0.4 km corresponds at about 4 turns
of the azimuth control knob. Note that this control has backlash which must
be considered in making azimuth adjustments.
Elevation adjustments over a range of about ±5 degrees are made by means of
a screw on the rear pad; see Figure If.2.1.2. Adjustments in elevation cause
the telescope image to move along the length of the entrance slit and are less
critical than the azimuth adjustments. Consequently, a coarser screw pitch of
18 threads per inch is used. The distance between the rear pad and a line
connecting the front pads is 38.8 inches. The elevation rate is, therefore,
(0.0555/38.8) = 0.001*4-3 radians per turn or 0.082 degrees per turn. For angles
exceeding the range of adjustment blocks may be placed beneath the pads although
this will usually not be as rigid as is normally obtained. An elevation mirror
being built on a follow-on contract will greatly facilitate paths which deviate
substantially from a horizontal plane.
In order to conveniently transport the stand assemblies, retractable wheels
can be lowered and the assembly rolled into place. The front wheel mounts are
fixed and the rear wheel mounts swivel. The wheels have zero-pressure pneumatic
tires to cushion shock loads during transport.
The front wheels are connected to triangular plates on each side of the
stand. A screw through each plate may be placed in either of two holes in the
frame to lock the plate in either the upper or lower position; see Figure 4.2.1.3*
The rear wheel mounts are connected to a shaft the position of which is controlled
by an arm on each side of the stand frame. A screw through each arm may be
placed in either of two holes in the frame to lock the arm in either the upper '.v
or lower position corresponding to the wheels down or wheels up position,
respectively; see Figure 4.2.1.3. Note that the screw should be placed in the
4-40
-------
Section A-A
Front Pad Detail
V
Ki
6.0
f-
Rear Pad Detail
Figure U.2.1.2 Stand Pad Details
-------
Front Wheel
Detail
Rear Wheel
Detail
Figure U.2.1.3 Stand Wheel Details
-------
hole in the arm before it is put into the lower position because of the
dose proximity of the lifting handle.
Lifting handles are provided to assist in controlling the stand during
transport and may be used during raising or lowering of the wheels. It will
be found convenient, however, in the latter case to use a laboratory jack
near the center of the frame. At the rear of the stand be sure the jack
clears the rear pad completely. At the front of the stand be sure the jack
does not interfere with the axle in the lower position.
The various electrical and coolant lines are grouped for convience at the
panel on the rear of the receiver stand. All of the connections are clearly
labelled; see Figure U.2.1.U* Convenience outlets for 110 volts 60 Hz power
are provided. Note that the plugs and jacks on the stand interface are
different from one another so that it is impossible to place a plug into the
wrong jack.
The reference blckbody is attached to a framework on the receiver stand by
four bolts. The blackbody may be removed either by removing these four bolts
or by removing the framework and blackbody as a unit. Access for blackbody re-
moval is obtained by removing the side panels.
Access to the synch receiver preamplifier and the mercury lamp power supply
is obtained by removing the right side panel.
System nameplates are attached to each side panel of each stand; see
drawing 596-722-018.
U.2.2 Auxiliary Stands
Because of the necessity of removing vibrating equipment from the main stands
it was decided to place some of the equipment (particularly that which vibrates)
in auxiliary stands. There is a source auxiliary stand and a receiver auxiliary
stand as shown in Figure U.2.1 and on drawing 596-722-019. The enclosures for
the auxiliary stands are Fjncor II units from.Ingersoil Products, Chicago, 111.
and are painted EN-2GO gold color.
Power lines and coolant tubing are routed down along the inside of each
auxiliary stand and extend from the bottom of the stand. A plate is used to
keep these lines clear of the drawer.
Equipment is secured to the shelves in the auxiliary stands by means of
one or more thumbscrews each which can be easily removed in order to permit
changes of equipment.
-------
o
To
Electronic
Console
Detector
O
OIn
Coolant
OOut
O
o
J113
J112
J105
AC Pwr
Input
Figure l|.2.1.U Stand Connection Panel
U-M*
-------
Electrical power is normally supplied to the auxiliary stands directly
and are protected by 15 amp circuit breakers located Just inside the rear
door of each auxiliary stand. The approximate current measurements are
as follows:
Start Run
Source Auxiliary Stand 13 amp 8 amp
Receiver Auxiliary Stand 17 amp * 12 amp
* if all equipment started at once; therefore, starting must
be staggered because of the 15 amp breaker.
H.2.3 Electronic Consoles
The electronic enclosures for the consoles are Emcor II units from Ingersoll
Products, Chicago, 111. and are painted EN-2GO gold color. Details of the
electronic, consoles and equipment locations are shown on drawing 596-722-020.
Electrical power is normally supplied to one electronic console and the
other console is plugged into the first. Junction strips are located just
inside each rear door of each console. The consoles are protected by a 15 amp
c&""d.t breaker. The combined 110V 60Hz current drain for both consoles is
15 amp starting and 12 amp running. Since all equipment is not started at
once the breaker should carry the starting currents.
Details of electrical interconnections are described in detail in Section
1*.3 and are collected for convient reference on drawing 596-722-033-
U.2.U KLackbody Plumbing and Mounting
The mechanical details of the first of several components, namely the black-
bodies, are given in this section. There are two blackbody units: one in the
source assembly and one in the receiver assembly. Each consists of three
parts: the blackbody housing, a closed cycle cooler and a temperature controller,
The interconnections of these three parts is.shown on Figure U.2.U.I. (note:
fan in blackbody apr o-ently deleted by manufacturer) The closed cycle cooling
loop is completed by two 3/8 inch diameter Polyflo plastic lines. Care should
be exercised in connecting the output of the cooler to the input of the black-
body housing and vice versa. The electrical connection for the source blacK-
body is made directly from the temperature controller to the blackbody housing
(as supplied by the manufacturer). No jack and plug numbers were assigned to
this simple connection for the source blackbody (the pin designations used
are identical to that of the receiver blackbody). The receiver blackbody
connections were run through the interface panel on the rear of the receiver
Btand for convenience. The correctors used there are identical to those on
the blackbody units as shown on Figure U.2.U.I. Therefore, the temperature
-------
Blackbody
Housing
Blackbody
Cooler
Coolant
Q O
\
Blackbody
Temp. Controller
Jl Pi
P112 J112
P2 . J2
Temp.
Controller
A
B
C
D
E
F
1
G
1
A
B
n
n
F,
F
G
Gnd
Heater
Heater
Fan
Sensor (-)
Sensor (+)
Fan
A
p
D
E
F
|
A
r>
D
E
p
1
1
A
D.
£
Blackbody
Housing
Figure h.2.k.l Blackbody Interconnections
U-U6
-------
Controller can be directly connected to the blackbody housing if desired
for bench testing, for example).
The blackbody housing drawing supplied by the manufacturer contains
errors and Figure U.2.U.2 is provided to show the blackbody housing geometry.
The internal plumbing of the blackbody housing is also shown on Figure k.2.k.2.
It should be noted that the blackbody plumbing supplied by the manufacturer was
partly made up of plastic tubing. Power failure would stop the coolant flow
and heat from the cavity would melt the plastic tubing inside the blackbody
housing requiring a tedious repair and cleanup„ Therefore, the plastic
tubing was replaced by copper tubing after obtaining permission from the manu-
facturer. Because the coolant fittings could not be removed from the cavity
itself it was necessary to make up a hybrid connector at the cavity. The half
of this connector nearest the cavity is half of the original connector and the
other half is half of a Swagelok connection. The two halves are silver soldered
together.
It was stated by the manufacturer that the plastic tubing on the outside of
the blackbody housing should not melt even with a power failure. However,
running the cooler for one hour after turning off the electrical power is still
recommended.
Start up and shut down of the blackbodies are described in the operation
section.
-------
Source
Chopper
(Source B,B.
only)
10.5
11.31-
10.38
8.31"
U.5
1.0
(Source
B.B. only)
8.5
7.75
5.5'
1.25
(RCVT,
B.B.
8.0only)
Figure U.2.U.2 Blackbody Geometry & Plumbing
-------
U.2.5 Telescopes
Although the telescopes axe primarily considered optical elements there are
a number of mechanical details which should be discussed. See Figure U.2.5.1.
The basic structural elements of Ane telescope are the primary and secondary
cell rings connected by a thin but st/:.ff shell. The primary cell ring not only
supports the primary mirror but olso *rves to distribute the loads to the tele-
scope mounting pads* The primary r,i?.?.-or is supported laterally by means of
three tie reds each of vrhich pass ?;hvcugh a radial hole in the primary mirror
substrate. The tilt of the primary txirror end its axial position are each
controlled by three screws at the hack of the primary mirror. The primary
mirror is spring loaded against these adjusting screws at each screw location.
The secondary mirror is provided with lateral and tilt adjustments which
are incorporated in the secondary mirror cell supported by thin vanes.
The telescope is supported at three locations on the rear face of the
primary cell ring. Taper pins at these locations ensure precise maintenance
of alignment. Bolts used to attach the telescope to the stand pass through
the stand pads and are screwed into tapped holes in the telescope ring. Care
should be taken not to overtighteii. these bolts thus stripping the threads in
the ring.
In assembling the telescope onto tho stand it is assumed that one person
will support each handle of the telescope and bring it close to the stand
aligning the taper pins and holes, Slide the telescope onto the taper pins
carefully so as not to bend them; as quickly as possible insert the bolt in the
top pad and tighten it finger tight, A':J this point the weight of the tele-
scope is supported and the two bottom belts ray bo inserted in a more leisurely
manner. Reverse the procedure for rea-nvg.! of the telescope. 'Again use care
in removing the telescope not to beuc' the taper pins» If the telescope sticks
to the stand a little prying and/or tapping will loosen it. If the taper pins
should get bent straighten them or if necessary they can be replaced.
^•2.6 Reference Optical System
Mechanical details of the reference optical system are described in this
section and are shown on drawing 596-722-03.0. The reference optical system con-
sists of the reference blackbody. a spherical nirror, a flat mirror on inter-
mediate focus assembly, a toroidal mirror. the reference chopper and supporting
structure.
-------
©
Figure l».2.5.1 Telescope General Assembly
U-50
-------
The reference optical system (except for the toroidal mirror and the reference
blackbody) is mounted on the front of the monochromator; taper pins ensure
maintenance of alignment. The toroidal mirror is mounted on the side of the
case of the detector optical system which is also attached to the monochromator
by means of taper pins. Thus alignment of the toroid relative to the rest of
the reference optical system is preserved even if components are removed and re-
placed. The reference blackbody was judged to be too heavy to support on the
monochromator; consequently it is mounted in a fixed position on the stand. After
adjustment of the monochromator-reference optics-detector optics assembly position
it is necessary to slightly readjust the spherical mirror of the reference optical
system.
In order to provide access to the reference blackbody for the radiation
probe it is necessary to remove the spherical mirror which is therefore
kinematically mounted. Holding down the spherical mirror mount assembly to
keep it from tipping, the three hold-down springs are released which permits
removal of the assembly.
The stem mounted flat diagonal mirror is adjustable for tilt by means of
three screws which push against the back of the mirror. The mirror is held
against the screws by means of a spring on the stem attached to the mirror.
The stem mounted toroidal mirror mount has axial and three tilt adjustments
as well as adjustable rotation about the stem mount axis.
The chopper is mounted on ultra-precision ball, bearings (which are pre-
loaded to eliminate axial play) in a housing to protect both the chopper and
operating personnel. The housing is mounted on a plate which is pivoted so as
to permit small variations of the nominal ^5° reflection angle. Three screws,
one below the baseplate, lock the chopper housing in position. Clearances be-
tween the chopper and reference synch elements within the chopper housing are
only about 0.03 inches; therefore, axial positioning of the chopper blade is
critical. The outer edge of the collar on the shaft end opposite the motor
should be flush with the end of the shaft. Axial pre-load is obtained by
pushing the opposite collar and pulling on the shaft with the fingers and
locking the collar set screw. Check to ensure the chopper turns freely before
energi-zing the reference chopper motor.
U-51
-------
U.2.7 Monochroraator
A number of mechanical modifications have "been made to the monochromator and
its attachment to the stand are described in this section. These modifications
include (in addition to the added entrance slit height assembly described in
the optical section) addition of a wavenumber shaft encoder and modifications
of the wavenumber drive.
The monochromator is attached to the plate of a mount (which is attached
to the receiver stand) by means of three bolts which also serve to lock the
mount plates together. Figure U.2.7.1 shows a detail of the connection. Access
to the monochromator attachment screws is required for removal of the mono-
chromator or for loosening of the adjustment screws in order to change the
monochromator lateral position. Such access is obtained by removal of one of
the stand side panels.
A shaft encoder was connected to the shaft which controls the grating
position and thus wavenumber in order to provide a direct reading of wave-
number. Drawing 596-722-015 shows the encoder installation underneath the
base of the monochromator. The encoder shaft is connected by an antibacklash
gear (1 to 1 ratio) to a gear mounted on the wavenumber shaft.
Modifications to the wavenumber drive are shown on drawing 596-722-013 and
include the following:
Replace 2 RBI motor with 3 RPM motor.
Stiffen one shaft in the wavenumber drive.
Remove unused marker switches wiring' and plug.
Change power plug.
Add a switch to permit driving the wavenumber shaft and
drum in either direction.
Provide electrical limits on both directions of wave-
number shaft travel.
The motor speed was changed to obtain the scan speed specified.
The unstiffened wavenumber drive shaft was so flexible that it resulted in
jerky rotation of the wavenuraber shaft at high scan rates. Stiffening this
shaft eliminated the jerkiness in the rotation rate.
Since the gear set-up in the wavenumber drive system is not described in
the.monochromator manual, Figure U.2.7.2 is included here. A convient scan
speed chart is provided on the top of the wavenuraber cover and is also shown
on Figure U.2.7.2. Since the gears are npt visible with the cover in place,
an index pin is provided in the chart to show the gear set-up in use. The
-------
Monochromator
Loosen
for
Lateral Adj
of Monochr.
Adjust
Height
Here
Lock Wut
Mount
Plate
Frame
Figure U.2.7.1 Monochromator Mount Detail
-------
Motor
N RPM
Wavenumber
Drum
Shaft D
UL
Ilk *
1:1 *
Shaft B Idler i Shaft C
Shaft A
N m N/k
A
Interchangeable
Gears
SI 2:1 *
S2 1:1 *
Sk 1:2 *
Selected by
Solenoid
Control
Ratio*
N
N
N/2
N/U
N/8
SI
2N
N
N/2
2:1
1:1
1:2
I:k N/16 N/8 N/16 N/32
* Ratio = Driver/Driven
'82
N
N/2
N/lf
N/8
Sk
N/2
N/lf
N/8
N/16
sf
6.0
3.0
1.5
N^CRPM) for N = 3 RPM
S2 Sk
3.0
1.5
0.75
0.75
0.375
0.375
1.5
0.75
0.375
0.1875
0.1875 0.09373
Wavenumber Drive Schematic
Gear Setup
Driver Driven
96
80
60
ko
2k
2k
ko
60
80
96
Ratio
kll
2:1
1:1
1:2
li*
WVNO
31
6
3
3/2
3/k
3/8
DRUM
S2
3
•^
3/2
3A
3/8
3/16
RPM
SU
3/2
3A
3/8
3/16
3/32
Wavcnumbor Drive Chart
Figure 4.2.7.2 Wavenumber Drive Details
-------
chart shows for each of the four available gear set-ups the three scan speeds
available for selection by the switch on the monochromator control panels
(SI is the fastest speed, S2 is the medium speed and Sk is the slowest speed).
The switch for changing the direction of wavenumber drive is located on the
side of the drive unit. Normally this switch will be in the up position for
which the drive will scan up in drum number and wavenumber.
-------
U.2.8 Detector Optical System
The mechanical features of the detector optical system are shown on Figure
U.2.8.1 and drawing 596-722-011. The components are located in a light tight
housing which is attached to the monochromator. Taper pins are used to ensure
precise positioning.
The toroidal mirror is mounted on the back housing plate and has three
adjusting screws for tilt control and a small axial motion of the toroidal
mirror.
The flat diagonal mirror is also mounted on the "back housing plate and can
be rotated in the mount and tilted to provide lateral adjustment of the image
on the detector.
The "Cassegrain" assembly is composed of two units: one large main unit is
used to support the concave primary mirror (to which is attached the field lens)
and the other unit consists of two concentric rings the inner one of which has
the small convex secondary mirror attached. Image symmetry is obtained by
lateral adjustment of this inner ring relative to the outer ring by means of
four pin-ended screws in the side of the outer ring which fit in the groove
in the inner ring. The distance between the "Cassegrain" mirrors and their
relative tilt is adjusted by means of three spring loaded screws in the top of
the outer ring. Dimensions for this "Cassegrain" pre-alignment may be obtained
from Figure U.I.5.1. The "Cassegrain" unit has been pre-aligned and should not
require realignment unless some catastrophe occurs.
The "Cassegrain" unit as a whole is adjustable with respect to the housing
in .the axial direction by means of 3 push-pull sets of screws. The lateral
position is retained by the close fitting pull screws.
Lateral adjustment of the detector relative to the "Cassegrain" unit is
accomplished by means of three screws in blocks on top of the housing which
push against the bottom flange of the dewar which contains the detector.
Before making such adjustments it is necessary to loosen the screws which
attach the bottom flange of the dewar to the housing enough to allow
relative movement but still snug. After lateral adjustment these screws are
tightened firmly and the focus of the "Cassegrain" unit is rechecked and
changed if necessary.
-------
60 ASSY.
*T# covilthZl) UMovED
Figure U.2.8.1 Detector Optical System Detail*
U-57
-------
U.2.9 Detector Mount-Dewar
Mechanical details of the detector installation on the detector cooler cold
finger are shown on Figure 4.2.9.1 and on drawing 596-722-016. Details of the
dewar in which the detector is mounted are given on drawing 596-722-009.
The detector is attached to the detector cooler cold finger by means of
four bolts. An indium shim is placed between the detector and the cold finger
to increase the heat transfer rate between them. The ungrounded detector is
electrically connected to two teminals on the dewar connector by means of 0.004
inch diameter constantan wire to reduce heat transfer.
The arrangement of the heater and sensor which control the cold head temp-
erature are also shown on Figure 4.2.9,!. These components are both mounted
with an indium shim also. Electrical connections are made to the instrumentation
ring connectors with Teflon covered copper wire placed along the cold finger so
as to tie down these wires thermally.
The bulb of a hydrogen vapor pressure thermometer is attached to the cold
head by means of a single screw; an indium shim is again used. The tube leading
to the gage is run down along the cold finger.
4.2.10 Detector Cooler
The Model 20 detector cooler was obtained from Cryogenic Technology Inc. (Cn),
Waltham, Mass, and used to cool the Hg: Ge detector to about 26K. It consists
of three units: a compressor and a temperature controller irsDunted in the re-
ceiver auxiliary stand and a refrigerator cold head mounted on top of the dewar
in which the detector is housed (see drawings 596-722-003 and 596-722-016).
The compressor is connected to the cold head by two helium lines and a
power line for the cold head motor; see Figure 4.2.10.1. The helium supply line
to the cold head has an oil absorber in it. The temperature controller is connected
to the heater and sensor through a plug on the instrumentation ring. The instr-
umentation ring also has a vacuum valve and a thermocouple vacuum gage attached
to it.
The refrigerator cold head has a cold finger which extends down through an
instrumentation ring into the dewar„ The detector and temperature control
heater and sensor are mounted on the bottom end of the cold finger.
4-58
-------
C.T.I. 385600U
Instrumentation Ring
596-722-009-60
Dewar Assembly
Sensor
Section BB
Figure '1.2.9.! Detector Installation
Section CC
Ji-59
-------
Terap. Control
Figure U.2.10.1 Detector Cooler Detaials
U-60
-------
4.2.11 Synch Systems
The mechanical details of the source synch receiver assembly are shown on
drawing 596-722-017. This assembly is attached by three screws to the receiver
telescope near the front at about 45° from.the top centerline on the right, side
looking toward the source. It should be noted that the shell of the detector
was removed to increase its field of view.
The mechanical details of the reference synch light emitting diode (LED)
and photodiode are shown on Figure 4.2.11.1. The LED and the photodiode are
each nounted on a printed circuit board which are attached to the chopper
housing. The LED board is identified by the letter "S" on the board upon
which the LED is mounted and the photodiode is identified by the letter "D"
on the board on which the photodiode is mounted. Care should be exercised
if repairs are necessary to keep leads below the board faces since the
clearance between the LED or diode and the chopper wheel is only about 0.032
inches.
U-61
-------
.\\\ \i\\\\\\.
%
\
ftV,v-'<'i'-J'^
E
r^^
\\\ V
k\\\\\N\^W^V\W
k\\\\\\i
V
S
— j
i
Figure U.2.11.1 Reference Synch LED and Photodiode
U-62
-------
I*.3 ELECTRONIC SYSTEM DETAILS
U.3*l The Electronic System
The electronic system design section gave a functional unit level description
and the relation of each unit to the overall system. Here each unit is con-
sidered as an entity and described on the component .level. There are two
types of units described: units designed and manufactured by General Dynamics/
Convair and vendor supplied equipment. GD/C equipment will be described in
detail as to physical location, dimensional size, circuit operation and inter-
connections with references to schematic and pictorial diagrams which are
included. Vendor supplied equipment will be described to the extent that it
has been modified or particularly applies to the ROSE system. Direction to
vendor manuals is given for mechanical and electronic details which are ade-
quately described and are consistent with the present hardware.
Topic headings used in this section have a one to one correspondence to
the system design section headings. For a functional description or the units
relationship to the system, refer to the corresponding part of Section 3.6.
U.3.2 Signal Sources
There are four signal sources associated with the instrument. A Hg:Ge detector
generates the source and reference signals. Two synch signals are generated to
provide frequency and phase reference for the signals. Additionally, an encoder
is used to generate pulses that are converted to a wavenumber representation.
Source and Reference - Hg:Ge
This signal source is predominantly optical in nature and the details given
here relate only to its electrical characteristics. For a further description
refer to the optical details section of this document. The bias requirement
of this detector is 1 ma, which is supplied through a 10K ohm 1% . precision
resistor (Figure ^.3.2.1) and a low pass filter to the +23.6 volt supply in
the preamplifier. The filter was added to reduce hum.
-------
r
Ijjiieuu —i ^r •-
„ -Input 1QK 1K
**vD
1%
1 i
^
-60 -v
+:23."6v ;
•PAR Model . -213 Prearap
.Figure-^.3.-2.1 Detector Circuitry
.The impedance. of the .detector is nominally "12.6K ohms -and the "detector is
•..connected'; by a. .coax .cable directly.to .the. high .'impe'dance :'input :of .the PAR
t-ixlel .213 ..preamplifier. .The shell .of .the.input connector :.anay Vbe - connected
,either to ground directly or, to reduce-/ground "loop ;current,, to,.ground through
a 10 ohm .resistor by means of a switch ..on the rear :oT Lthe jprearaplifder.
Source and Reference Synch Detectors
The purpose of these ..two detectors 'ds to provide a signal .which -can 'be.ampli-
fied into saturation to provide a synch signal for the "'lock-in .-amplifiers.
The .source synch detector is -an Electro-Nuclear ..Laboratoziies., .Inc. ::Type 632
-Indium.Arsenide .(InAs) photovoltaic .detector. The (.detector .-is mounted on the
receiver telescope housing and interceptsra^portion of the source-beam. The
1.5 ma active area is insufficient to provide ^ade_quate .signal in .the .long path
conditions. '.Therefore, it is.mounted behind• a -collecting lens system. The
detector has an impedance of 20 ohms which 'is 'transformer -coupled up :.to 100 KD
•by a UTC A27 ,tr?.nc former vrhich .is located .'inside 'the receiver ^s'tand. At this
point the output; of the transformer drives a preamplifier '(s'ee the .-next section),
The only electrical connection to the "detector .is a coaxial cable rtha't carries
the signal to the transformer.
The reference synch defector is a Hewlett Packard (H.P.) '5032-^205 Photo
Diode. It is located opposite a H.P. 5032-410? GaAs infrared source and both
are perpendicular to the plane of the reference chopper which passes "aetwcen
U-6U
-------
them. The source emits in a narrow spectral region around 0.9^ which is near
the peak response of the photo diode. The source is forward biased by con-
necting it through a 68n resistor to +6 volts. Forward current in the source
is 80mA, producinc an emittance near 80$ of peak. The reference synch detector
diode is reverse biased by connecting it to -15 volts through a 51* ohm
resistance. The interconnections for the reference synch detector arc .schemat-
ically represented in Figure 4.3.2.2. While the source synch signal requires
preamplification the reference signal is large enough that it is directly
connected to the synch amplifier in the console.
Jill Pill J10U PlOk P103 J103
Stand
> /• Q
> DO
kw£
V Q
T
n
P
T)
1.
4
7
1
i.
4
7
2
}.
4
7
2.
i
k
7
DOX.
SloA
SloF
0*1 fti"1
Slot, •
+ 6v DC
Synch /ijnp Input
Synch Amp Input -'
Stand Logic Box "
Interface
Figure 4.3.2.2. Reference Synch Detector
V/avenumber Generation - Shaft Encoder
A Dynamics Research Corporation Model 35 digital incremental shaft encoder is
the signal source used to generate wavenumber. The particular encoder used
generates nine thousand pulses per encoder shaft revolution, whijh is also one
shaft revolution of the monochromator (see mechanical details section). These
pulses in conjunction with the wavenumber logic provide wavenumber input
information to the counter. The encoder itself generates sine waves on two
-------
lines which have a 90 phase relationship. An electronics option provided on
the encoder senses the phase relationship and gives output pulses on the C.W.
output for C.V/. rotation and on the C.C.W. output for C.C.W. rotation. The .
complete part number including the optional electronics is 35-1-001-900. The
appropriate specifications for this part number are tabulated in the table
below. Figures U»3.2.3 and U.3.2.U give the interconnections of the encoder to
the system and encoder dimensions respectively:
Input Voltage:
Input Current:
Output Waveform:
Output Offset:
Output Amplitude:
Output Rise Time:
Maximum Output Frequency:
Maximum Output Current:
+6 ±0.3 Vdc
-6 ±0.3 Vdc
+6 Vdc 390mA
-6 Vdc l*5mA
Square
0.3 ± 0.3 Vdc
5.9 ± O.U Vdc
< 2|o, sec
20K Hz
Encoder Specifications
J109 P109
J106 P106
P10U P103 J103 Logic Box
Encoder
f
t\
C
11
J
K
L
A
C
H
J
K
L
C.V7.
C.C.
Outtmt
W. Output
-6v
+6v
cm
1
2
3
U
5
,
1
2
3
k
5
1
10
3
2
7
1
10
3
2
7
Stand Stand
Interface
1
10
3
2
7
1
10
3
2
7
Logic
Box
,,
S22-P ~]
S22-13 J
S17-A 1
S16-A J
1
Figure ^.3.2.3 Encoder Interconnections
U-66
-------
From the above specifications and interconnection diagram it can be seen
that the encoder output directly drives the counting logic and that sufficient
drive exists so that no signal conditioning is required.
1.6500
Figure U.3.2.U. Encoder Dimensions
U-67
-------
U.S.3 Signal Amplifiers
In a manner similar to that used in the electronic design section, the source
and reference amplifier chains are treated in a separate subsection from the
synch signal amplifiers. Again the paragraph numbers correspond to the numbers
in the design section where the system relationships are discussed.
Source and Reference Signal Amplification
The mixed source and reference signals are initially amplified together in a
PAR Model 213 preamplifier.
PAR Model 213 Preamplifier
A manual for the instrument is supplied by PAR and this section is therefore
limited to specific details related to this application. The Hg:Ge detector
has an impedance of 12.6K ohms which dictates use of the high impedance input
of the preamp. This detector impedance coupled with the nominal operating
frequencies ^ives the preamplifier a noise figure of about 2 db. The pre-
amplifier is normally plugged into a NIM BIN which supplies power from its
integral power supply. However, in the ROSE system the preamplifier is mounted
on the interface panel of the receiver stand. This was done to minimize lead
length from the detector to the preamplifier. The preamplifier is powered by
the NIM BIN power supply through a remote cable as indicated in Figure U.3.3.1.
Jl
NTM BIN
Control
Panel
(Rear)
.15 PH5 P113 J113 PllU Jl]
5
7
6
3_
5
7
6
+2UV
_ 2kV
Gnd
IT
A
B
C
A
B
C
*
28
29
3»»
28
29
31*
.U
PAR 213
Preamp
Stand
iterface
Dir
'Jnr
>*-
3—i
•*
BNC 8?
•ect
)Ut
Detecto
Output
Figure U.3.3.1 Preamplifier Intercomv. ctions
U-68
-------
The output of the preamplifier is a ENC front panel connector. The output
is connected by coaxial cable to ENC No. 8? on the rear of the control panel,
at which point it is connected to the "operate" position of the STD. SIG -
OPERATE switch. The wiper of this switch (in the "operate" position) connects
the preamplifier output to ENC 88 on the control panel from wliich the signal
goes to the input of the selective amplifiers.
PAR Model 210 Selective Amplifiers
A vendor supplied manual covers most of the detailed information of these
amplifiers and should serve as the primary source. The details here relate
only to the specific application information. Two Model 210 amplifierc are used
in the system and they are located in the console NXM BIN. Only the signal
wiring is of concern as they obtain power from the integrated supply in the
NIM BIN. The source selective amplifier (which is mounted at the left looking at the
front of the console) has its BNC input at the rear connected to the wirier of
the STD. SIGNAL - OPERATE switch (i.e., calibrate or preamplifier output). The
connection is made through a coaxial cable to ENC No. 88 on the control panel which
is connected to the switch wiper. The BNC labeled "input" on the front panel is
in parallel with the rear panel BNC and is used to jumper the input signal to the
reference selective amplifier input. The selective amplifier outputs of interest
here are the resonance outputs. This output is the signal, with a bandwidth
determined by the "Q" setting, at the frequency to which the selective amplifier
is tuned. These outputs are connected by coaxial cable to the signal input ENC
connectors of the respective lock-in amplifiers. These signal connections are
illustrated in Figure ^.3.3.2.
Source
Reference
Control Panel
BNC 86
BNC 8?C
Std. Signal
Operate
BNC88
210
Sel.Amp
— i
(
(Rear)
) Input
Resona
_L
220A
Lock- In
Sig
C
nee
1 J
In
>
210
Sel. Amp
(
"> Input
Resona
_L
220A
Lock- In
Sig
C
nee
I j
In
j>
Figure ^.3.3.2. Selective Amplifier Signal Connection:;
-------
The "Q" value used should be selected with two factors in mind. First,
the function of the selective amplifiers is to provide signal separation and
to prevent overload of the lock-in amplifiers. This would indicate the use
of a high value of Q. However, gain stability is inversely related to Q and
stability is important. Since the. selective amplifier response time increases
with Q a maximum value exists which is a function of scanning speed. Selection
of the proper Q setting is discussed more fully in the Operation section.
PAR Model 220A Lock-In Amplifiers
The Model 220A was not a standard PAR amplifier at the time this instrument
was designed. It was a significant modification of the Model 220. As a con-
sequence the front panel markings and manual supplied were for the Model 220.
Specifically in the modification, overload capability, sensitivity and long
time constants were sacrificed in favor of low noise and baseline stability.
This resulted in a much better amplifier for this application, because of the
frequent occurrence in this application of signals that are a small percentage
of full scale.
Templates were made to attach to the front panel so that the true values
of sensitivity and time constant are indicated. The manual has been
updated by the inclusion of a note page and "marking up" the manual to indicate
the changes. This allows the manual to be considered the prime source of
detailed information related to the lock-in amplifiers. Power for the lock-ins
is again supplied by the HIM BIN power supply. External wiring associated
with the amplifiers consists of only input signal, synch signal, and output
signal coaxial cables. Input signal cables connect the resonance output of
the selective amplifiers to the "signal input" of the lock-in amplifiers as
shown in Figure 4.3,3.2. The output signals are connected by means of coaxial
cable from the "monitor" BNC connector to the respective "lock-in amp. input"
BNC connectors on the control panel. Adjustable amplifier parameters such as
frequency, phase, time constant, sensitivity and mode must be adjusted accord-
ing to the operating conditions of the system. The Operation section of this
report explains the proper settings for these controls.
Voltage Followers and Compensation Amplifiers
The voltage follower amplifiers are unity gain amplifiers of GD/C design
used to decrease the output impedance of the lock-in amplifiers. They are
inserted in each amplifier chain because the output impedance of the lock-in
amplifierc is [}K ohms while the compensation amplifier should be driven from
les.s than fjQ olims. A circuit board located at S19 in the logic box contains
both the voltage followers as well as the compensation amplifiers. For this
reason they are discussed and illustrated as a single amplifier. A schematic
diagram of the combined voltage followers and compensation amplifiers appears
as Figure ^.3.3.3. Drawing 596-722-02? contains a schematic, component layout
U-70
-------
and connector wiring. Reference to Figure U.S.3.3 is made in the text on
circuit operation, while trouble shooting would require the drawing for com-
ponent location purposes.
•-'w i
Figure ^.3.3.3. Source and Reference Compensation Amp
The two voltage follov,rers use one Fairchild pA7^7C dual operational
amplifier. The inputs to the voltage followers from the lock-in amplifiers
are to the non-inverting input. The resulting gain is
-------
1 Rt 1 * —
A = 1+" = X +
A = 1 + -T — =
. 2H9K
which is considered to be unity gain. The output impedance of the voltage
followers is significantly less than 1 ohm and considered to be zero. The
source and reference compensations amplifiers also jointly share a uA7^7C
amplifier with the source compensation amplifier being the lower one in
Figure U.S. 3. 3. The source amplifier is simply another non-inverting amplifier,
with the input controlled by the SIGNAL T ADJUST potentiometer. The source
voltage follower output appears at (K) and the source compensation amplifier
input at (r). The source compensation amplifier gain is eight as determined
by the non-inverting amplifier gain equation given above. A gain of eight is
used for a number of reasons which include the dual chopping of the source,
signal loss due to the atmospheric path and vignetting. These factors are
discussed in the Radiometry section 3«3-3«
The reference compensation amplifier is a unity gain differential amplifier.
Its purpose is to "decontaminate" the signal from the reference voltage fol-
lower which contains contributions from both the source and reference beams.
The undesired source beam component can be cancelled out by using a nearly
identical component from the source beam in an initial balancing procedure.
Refer to the Radiometry section 3.3 for further details. The gain at the
inverting input (Pin l) of the amplifier is
Rf _ R8
A = Ro ~ R7
A - 1
while the gain at the non-inverting input (Pin 2) is
Rf , R8
A - l + = 1 +
A -
U-72
-------
A voltage divider Rll and R12 is used to reduce the input to Pin 2 by
one half. Thus, the gain of both inputs with respect to the voltage follower
outputs is unity as desired.
All the resistors in this circuit are 1% metal film resistors for gain
stability. The potentiometers Rl, R2, R3 and RU are ten turn potentiometers
used to adjust the offset of each amplifier to zero. The circled numerics
are the test points located on the circuit board, while the alphanumerics
are the pins on connector S19. The output impedance or the compensation ampli-
fiers is less than 1 ohm allowing the amplifiers to directly drive the data
acquisition system. The interconnection of this circuit to the system is
adequately documented in the wiring tables.
Synch Signal Amplification
There are two synch signals: the source synch and reference synch. The source
synch signal is amplified in a chain consisting of a coupling transformer,
source synch preamp, 120 Hz gyrator, and source synch amplifier. The reference
synch signal is simply amplified by the reference synch amplifier.
Coupling Transformer
The output of the In As source synch detector is connected by a coaxial cable
to the input of an impedance matching transformer. The transformer a UTC
Type A27 with A-33 shield serves two purposes. First, it provides an
approximate match of the 50 ohm output impedance of the detector to the source
synch preamplifier input impedance of 1 megohm. It also serves as a low noise
signal amplifier.
The A-27 as installed in this application has a primary impedance of 50 olims
and a secondary impedance of 100K ohms. The voltage gain (primary to secondary)
is U5 which produces a worst case signal significantly above the preamplifier
noise level. The transformer is physically located inside the receiver
assembly stand. The output of the transformer is connected by coaxial cable
to the source synch preamplifier.
Source Synch Preamplifier
The source synch preamplifier is a GD/C designed circuit used for low noise
amplification of the source synch signal. It muct provide a synch signal of
sufficient amplitude so that signal to noise ratio will not be degraded by the
gyrator or other following circuits not designed for low noise operation.
Physically the preamplifier is in a mini chassis shared with the gyrator and
located in the receiver assembly stand. Input signal is .from the coupling
transformer and its output is the fed to the gyrator. Figure U.3-3^ 1S a
schematic of the preamplifier and is referred to in the discussion. For trouble
shooting and component layout information drawing 596-722-023 should be utilized.
-------
s»
~7V
.Cl ,
Btfff <
1
^b
" <
,/»< <
;
Ml*,
f
<
<
Lej
•if/"
>«»
>>«•<
-r
**
H*
xe
ii*
,_
«r ],. <
*< y?»%/ *
A?
/.«!«.
4P
>
-------
The second stage gain is modified by the unbypassed source resistance and is
found by the expression
AV
gm Ros R
d
2 Ros 4 (gm Ros + l) R + R,
s d.
where gra = actual gm from gm vs I curves
Ros = output resistance
R = load resistance
d
I = 0.3 ma
d
R = unbypassed source resistance
The gain of the second stage is
850 upho x UOOK x 21K
AV
2 400K + (850 ppiho x *K)OK + l).55K + 21K
=12
With the emitter follower gain of one the total preamplifier gain is 321*.
The amplifier is broadband but the predominance of 120 Hz noise over shadowed
its inherent low noise capability. This necessitated the use of a narrow band
filter. Using a gyrator required a relatively high input impedance for
stability. The large value of emitter resistance in the emitter follower
reflects this requirement. Input, output and power line interconnections
associated vrLth the preamplifier are shown in Figure U.3»3»5»
U-75
-------
• — v
J —
(
21
1
9
6
3
2
+2UV
L Gnd
^ l^Sig OutK
r,, \
'
II
A A A A.
AV
ayrator
A
B
C
D
1U
17
20
21
Co
Traj
Gnd
Sig In { \
** ^y
Jll6
+2UV i,
-2UV *
upling
ns former
P116
I
1»
'6
Source
Preamp
Synch.
Prearap
Figure ^.3.3.5. Source Synch Preamplifier Interconnections
120 Hz Gyrator
The gyrator circuit is contained along with the source synch preamplifier
in a mini-chassis located in the receiver assembly stand. Its primary
purpose is to filter out 120 Hz noise from the source synch signal. 120 Hz
gyrator is a misnomer; it is really a notch filter using a gyrator as the active
element. Circuit diagram Figure ^.3.3.6 shows three operational amplifiers,
two of these are contained in one dual-in-line package. The nA7^7 is a Fair-
child Semiconductor dual operational amplifier with internal frequency com-
pensation. A pA7^1 is identical to I of a nA7^7. The two halves of thepA7U7
form the notch filter while the pA7^1 is an inverting amplifier providing gain
and a low output impedance. Simple interpretation of a nomagraph included
vdth an application note gives the value for the frequency determining
-------
Figure U.S.3.6. 120 Hz Gyrator
capacitance of 01, C2 and C3 in parallel. Parallel capacitors were used to
obtain the required .035pfd because the value is quite critical in this high
Q circuit. Zener diodes Dl and D2 along with their bypass capacitors C9 and
CIO provided a ±12 volts D.C. power supply for the operational amplifiers.
The inverting amplifier has gain equal to 120 and output impedance less than
0.5 ohms.
Drawing 596-727-02U should be referred to for component layout and con-
nector information on this circuit. Interconnection of the gyrator to the
system is illustrated in Figure ^.3.3.7. The input signal is the output of
the preamplifier while the output is cabled to the console and becomes the
input to the source synch amplifier.
-------
J115P115 PH3 J113
P116
NTM
BIN
+?Uv '
55
-24V „ ' rj
1
A A
B B
1
NIM BIN Stand
Interface
318 J103 P103 P10U J10U
1
L_. . f f .., ,
o 0
1
16 16
6 6
1
Synch Amps Logic Stand
Box Interface
6
2
1
6
2
Sig
Output
1
2
3
B
18
Sig Input
Gnd
D
21
20
"
Synch.
-2I1V
,?hV
Source Gyrator Preamp
Synch.
Figure H.3»3«7. Interconnection of Gyrator
Source Synch Amp
The source synch amplifier is physically loca.ted in the logi': ••'.hassr.s of
the console. It shares a circuit board located in Sl8 with the reference
synch amplifier. A schematic shovang both the source synch amplifier and
reference synch amplifier appears as Figure U.3.3-8- The lower amplifier
consisting of two operational amplifier stages is the source synch amplifier.
Drawing 596-722-026 shows component locations and the combined schematic
diagram. Use of this drawing will facilitate trouble shooting and. aiiiTUirf.er
offset adjustment.
u-78
-------
Figure ^.3.3.8. Source and Ref. Synch Amplifiers
The first stage is a high gain inverting amplifier using a yA725 instru-
mentation amplifier. This gain, determined from the inverting amplifier gain
formula is 160. Capacitor C5 which bypasses the feedback resistor makes the
amplifier a low pass filter. The corner frequency of C5 and Rl6 determines
a pass band from zero to 720 Hz. Components C6, C7, PJ.7, and Rl8 make up the
frequency compensation network for the yA725. Variable resistor R15 is the
offset adjustment and may be adjusted to optimize the output for various input
conditions. Tlie output of this stage drives the inverting input of the nA7^1
through R19 and C8. R19 and C8 are a high pass filter with a corner fre-
quency at 3^0 Hz. At this point in the amplifier chain the signal is saturated
or near saturation meaning the amplitude is ±1^ volts B.C. The gain in the
second stage is generally academic but v/ould be 1000 up to the corner frequency
determined by C9 and R21. This corner frequency is rather hard to determine
because input to output capacity is significant compared to 100 pf; it is
approximately IKJlz. This stage is more important for the low output impedance
U-79
-------
18
B
Gyrator
it provides (i.e.,< in) than for its gain characteristics. The overall
effect on the signal due to the source synch amplifier is that the com-
plete range of input signals appears as ±lUV square waves at the output.
Therefore any changes in source synch signal amplitude, noise or wave shape
does not affect the reference input to the lock in amplifier. Figure
^•3-3-9 is an interconnection diagram for the source synch amplifier.
J116 P116 J10U P10U P103J103
S20
6 6
16 ' 16
I
6 6
16 ' 16
Sig. In
Gnd
Source
Synch.
Preamp.
Stand
Interface
Gnd Buss
-15V Buss
+15V Buss
L
B
Z
B
A
C
B
C
Cal. Sig.
Generator
BNC 97 BNC 8U
Synch
Amplifier
BNC
Source Synch.
Det. Output
Figure ^.3.3.9- Source Synch Amplifier Interconnections
Reference Synch Amplifier
Input to this amplifier is the reference synch signal generated by the Ga As
diode detector associated with the reference chopper. The output from this
detector ir. of sufficient amplitude so that a single operational amplifier
stage will provide ad'-: ate signal. This circuit is located at Sl8 in the
logic box of the control console. It shares this circuit board with the
source synch amplifier. For this reason it also shares a schematic diagram,
Figure U.3.3.8 in this section, and Drawing 596-722-026. The top half of
Figure U.3.3-8, the single uA?25 instrumentation amplifier is the reference
synch amplifier. It is an inverting amplifier using proportional feedback.
Gain of the amplifier is a function of the voltage divider on the output as
well as the feedback ratio. An expression for the gain is
U-80
-------
A =
Rout
RSEN
Rf
RIN
R7 + R8
R8
£1
R3
A =
100K + IK
IK
1M
10K
= 10
This gain figure of 10 is restricted to frequencies within the amplifier
pass band. Capacitor CIO and resistor R2 set the low frequency corner at
870 Hz. Capacitor C2 and resistor R5 set a high frequency corner at 1300 Hz.
All other components in the circuit do not reflect on the gain. The network
consisting of C3, CU, Rll and RIO is the frequency compensation network for
the uA725- Variable resistor R6 which is mounted on the back of the Sl8 board
is for offset control. Biasing and coupling characteristics of the input
signal determine an optimum operating point. Operating point or offset is
controlled by R6. It should be adjusted for an output square wave with mini-
mum noise and rise time. The network consisting of R9 and Cl provides a return
path and supply voltage filtering for the HP)4205 diode detector. The output
of this circuit serves as the reference lock-in amplifier's reference signal
and also provides reference frequency input to the calibration signal gen-
erator.
Figure U.3«3«10 gives the interconnection of this circuit to the system.
Jill Pill J10U P10U P103J103 Sl8
S20
1
c c
1
D D
Stand
U U
5 5
Stand
Interface
u'u
5 5
15V BU3S
Gnd Buss
+15V Busc
E
F
J
A
B
C
Sig Out
'
Z
B
BN
Cal. Sig.
Generator
fC 98 BNC 85
\ X|
*^s
Ref. Sync!;.
Det. Output
Figure U.3.3.10. Reference Synch Amplifier Interconnections
'*-8l
-------
U.3«^ Wavenumber Generation
The system design section of the document discusses the theory of the design
and should be referred to for an understanding of overall operation. In
this section block portions of the logic associated with wavenumber genera-
tion will be discussed in detail. Drawing 59&-722-032 is to be referred to
in all paragraphs related to wavenumber generation. All board type numbers
refer to the Data Technology part number.
Pulse Shaping Logic
The pulse shaping logic and all other logic functions related to wavenumber
generation are located in the logic box of the control console. Circuit boards
S22, S23, S2h contain the pulse shaping logic. Physical location of these
boards inside the logic box may be found on the card layout diagram in
the front of the wiring table. Inputs to the pulse shaping logic are the clock-
wise (CW) and counterclockwise (COT) pulses from the shaft encoder. Clockwise
pulses are connected to S22 Pin P and to S2U Pin N. Board S22 is a Data Technology
circuit containing three quad dual gates. S22 Pin P is one input of a dual in-
put nand gate while the other input Pin R is the output of dual gates wired as
a flip-flop. Gate A2-S will go to "0" if both inputs P and R are "1". P is of
course "1" at each CW input pulse. R is "1" if the previous input pulse was
also a CW pulse. This results in an output at A2-S each time a CW pulse occurs
preceded by a CW pulse. Pin R is held at one by consecutive CW input pulses.
This is accomplished by having the input at Pin N of S2U trigger a monostable
on its falling edge. Board S2k contains monostables used by the pulse shaping
logic. These monostables share board S2^ with the Data Control monostable.
For a schematic diagram refer to Figure U.S.U.I and for component layout refer
to drawing 596-722-031. The U.5 u,sec vide output of the monostable at Pin P of
S2U is inverted by A3-U on S22. This inverted pulse at Pin U of S22 sets a flip-flop
consisting of gates A3-Z and A2-22 so that S22 Pin Z and hence, S22 Pin R are "1".
Each consecutive CW pulse will then appear in its inverted form at S22 Pin S from
where it is connected to the coarse counting logic, and to Pin 7 of S23. S23 is
a Data Technology 5^0 one shot multivibrator. Pin 7 is the input to one of these
one shots and has Pin h as the output. The result is that Pin k is a delayed
form of the pulse used to drive the coarse counting logic. This delayed pulse
is used to drive the fine counting logic which insures that both coarse and
fine count logic cannot have an output simultaneously. With the above set of
conditions should a CCW pulse appear it would not get to the counting logic.
This is true because S22 Pin lU is "0" and hence gate A2-15 is disabled. How-
ever, similar to the CW pulses this first CCW pulse trailing edge would set
the flip-flop so that S22-22 would go to "1". This would then enable A2-15
and the next CC:.7 pulse would reach the counting logic. The outputs of gates
A2-5 and A2-15 are wired together forming a "wired OR" circuit. A "wired OR"
is used because there is but one set of counting logic and it needs to be driven by
-------
both CW and CCW pulccs. This dual utilization of the counting logic saves
counters but necessitates a circuit to sense and remember which direction
is providing input to the counters.
Direction Sensing Logic
The direction sensing logic consists of boards S22 and S23. They are Data
Technology 502 quad dual gates and a 5^0 one shot mcnostable multivibrator
respectively. The direction sensing logic serves two functions. First, it
steers the output of the counting logic to the counter (X) input or counter
(Y) input for CW or CCW encoder inputs respectively. CW rotation corresponds
to an increasing wavenumber and bidirectional counter input (X) increments
the count. CW rotation corresponds to a decreasing wavenumber and the (Y)
input decrements the counter. This results in the counter properly tracking
the wavenumber. The second function of the direction sensing logic is to
enable the resolution counter only during CW rotation to avoid backlash pro-
blems. This is accomplished by inverting the counter (X) input and using it
to drive the resolution counter. Counting logic output steering is accomplished
by use of a monostable and a dual input gate. The CW input line is connected
to S23 Pin 13« This is a monostable input whose outputs are at Pins 19 and 12.
Pin 19 is the input pulse stretched to 4.5 microseconds. Pin 12 is the "not"
of Pin 19. The sum of the counting logic output is at S22 Pins 5 and 6 which
are inputs to two different gates. S23 Pin 19 goes to S22 Pin 4 and S23
Pin 12 goes to S22 Pin 7. The result is that following a CW input pulse gate
Al-3 of S22 will be enabled for 4.5 microseconds by the output of the mono-
stable. All counting logic outputs would appear during this period at gate
Al-3's input and be steered to the counter (X) output. If the counting logic
output was due to a CCW pulse the "not" CW function at S23 Pin 12 would enable
Al-8 of S22o This would then steer the output to the counter (Y) output.
The resolution counter input is provided by inverting the output of Al-3«
Al-3 is connected to Pin F of S22 which is the input to gate Al-J. The inverted
signal at Al-J is then connected to the resolution counting logic input at
S10-C.
Counting Logic
The purpose of the counting logic is to convert the 9K pulses per revolu-
tion outputted by the pulse shaping logic into the number of pulses per re-
volution set by the encoder control switches on the control panel. Each of
these switches, "coarse", "tens", and "ones" controls a, separate counter in
the counting logic. The counting logic output vail be the sum of the numbers
set by the switches. The components of the coarse counting logic include tv.'O
528T binary counters, board numbers Sll and S12; Sll is the coarse counter
for the 7-13.5n region and S12 is the coarse counter for the 3-5.5o. region.. A
4-1
-------
quad dual gate type 502T, board number S13 and a dual triple input gate type
503T, board number S8 sum the various binary outputs of Sll and S12 to form
the proper factors. A quad inverter type 501T, board number S15 is used to
reset the counters Sll and S12. The remaining components of the coarse
counting logic are the two coarse selector switches, one for each spectral
region, located on the control panel. The output of the pulse shaping logic
"OR" gate at S22 Pin S drives both counter inputs located at Sll and S12 Pin C.
The outputs of the counters are tied to gates so that a desired division factor
is acquired. For example, the Q2 and Q5 outputs of Sll are summed by gate
Al-8 of S13. After 18 input pulses both Q5 and Q2 will be "1" and Al-8 will
go to "0" at its output. The output then resets the counter. Hence gate Al-8
will have an output every l8 input pulses which is equivalent to 500 pulses
per shaft revolution. When the instrument is in the 7-13«5u-.mode and if the
7-13.5P- coarse selector switch is in the 500 position the Al-8 output will be
the coarse input to the counter. It must however be summed with the tens and
ones counts in the counter output logic. The 529 coarse count associated with
the 7-13.5u- region is formed by gate Al-3 of S13. The inputs, to Al-3 are the
05 and Ql outputs of counter Sll. Every 17 input pulses will produce an out-
put at Al-3 and hence, 529 counts per shaft revolution. Counter Sll is reset
by double inverting the wiper of the 7-13«5p< coarse selector switch. The
wiper is connected to an inverter A2-7 of board SI5 which has its output con-
nected to A2-9 of S15. The output of A2-9 is tied back to pins k, 8, 12, 16,
L, R, V, and Z of the Sll counter and hence, resets the whole counter. The
result is that counter Sll will divide the input 9K pulses by 17 or 18 de-
pending on the selected 529 or 500 position of the course selector switch
respectively. Counting output will be present at the switch wiper and be avail-
able for summing with the tens and ones counts. Counter S12 works in a similar
fashion for the 3-5«5n region. The division factors required for 1125 and 1286
counts are 8 and 7 respectively. A factor of seven is obtained by summing
the Ql, Q2, 03 outputs using gate Ak-V on S8. A factor of eight is obtained
liy inverting the QU output with gate Al-J of S13. Resetting of counter S12 is
again similar to the reset of Sll. The wiper of the 3~5«5y, coarse selector
switch is double inverted by gates Al-3 and Al-E of SI5 and connected back to
the reset lines Pins h, 8, 12, and 16 of S12. Again the wiper will have the
selected counts on it and be available for summing with the tens and ones
counting logic output. Tens and ones counting logic uses the same technique
as the coarse counting logic. The tens logic consists of two 528T counters,
board numbers S5 and S6, three types of summing gates a 50UT at (S7), 503T
(s8)and a 508T (S9), inverter type 501T (S15) for counter reset and the tens
selector sv.-itch on the control panel. Tens counts of 0, 10, 20, 30, 80, 90,
100, 110, 120, 130, lUO, 150, and l6o are available to be selected by the
-------
selector switch. The discontinuity in values is accounted for by the total
count requirements. When the instrument is operated in the 7-13.5p, recion
the total 0.1 vavcnumbero per revolution will be between 500 and 560 with
520 being the norraniil value experienced. The use of the 500 or 529 coarse
count plus the 0, 10, 20, or 30 tens counts will cover this complete range
of values. Operating the instrument in the 3-5.5u recion will require between
1210 and 1310 0.1 wavenumbers per shaft revolution. The coarse values 1125
and 1286 along with the tens made available will cover all cases in this range
of values. The nominal value experienced was 1265 0.1 wavenumbers per
revolution. Input to the tens counting logic is the delayed encoder pulse
from the 5^0 monostable board S23 Pin k. The input is connected to Pin C of
the S5 counter. Input to the S6 counter is the output of the S5 counter
meaning S5 Pin W to S6 Pin C. This serves to extend the length of the
counter by two binary bits. Ql and Q2 outputs of S6 then become effectively
the Q9 and Q10 outputs of the tens counter. To summarize the following tens
counting logic table is shown to provide input, gate and board information
for each of the 10fs counts.
Summing Gate Counter
Count/Revolution Board Location Gate Inputs
10 S7 A1-1I Q2, Q8, Q9, Q10
20 S? Al-3 01, 07, 08, Q9
30 S9 Al-9 01, 02, QU, 06, Q9
80 S8 Al-F Ql, Q6, Q7
90 S8 Al-3 03, 06, Q7
-LOO S7 A2-N Q2, QU, Q5, Q7
HO S8 . A2-L Q2, Q5, Q7
120 S7 A2-8 Ql, Q2, QU, Q7
130 S8 A2-7 Ql, 03, Q7
1^0 S8 A3-R Ql, Q7
150 G7 A3-U Q3, Ql*, Q5, Q.6
160 S7 A3-13 Ql, Q^> 05, Q6
Reset of the tens counting logic is similar to the coarse counting reset.
When an output appears at the tens selector switch it connects through invert-
ers to the reset lines. Specifically the wiper is connected to gate A2-lh on
board 315. It is reinverted by gate A2-K and connected back to S5 Pins U, 8,
-------
12, 16, L, R, V, Z and to S6 Pins h and 8. Thus, with each tens output pulse
the counter consisting of S5 and S6 is completely reset. The output pulses
on the tens selector switch arc also the tens counting logic output and are
sunned with the coarse and ones outputs in the counter output logic. The
ones counting logic is nearly a duplicate of the tens counting logic. The
input is the delayed encoder input from S23 Pin h to the counter input at
SI Pin C. The 528T counters at SI and S2 form a single long counter with
Ql through Q6 of S2 actually being Q9 through Ql^ of the combined counter.
The summing gates of the ones counting logic are a 508T located at S3 and a
50UT at SU. Counter reset is again provided by inverters 501T on board S15«
The table below is provided to summarize the output count, summing gate board
location, gate number, and the counter inputs to the gate.
Summing Gate Counter
Counts/Revolution Board Location Gate Inputs
1 Sk Al-H 06, 09, Q10, QlU
2 SU Al-3 05, 08, Q9, 013
3 S3 Al-9 02, Q3, Q5, Q6, Q8,
09, 010, Q12
h Bk A2-N QU, Q7, 08, 012
5 S3 A2-18 Ql, Q2, Q3, 09, 010, Oil
6 S3 A3-P 01, 02, QU, 05, 07,
08, Q9, Oil
7 SU A2-8 01, 03, 09, OH
8 S4 A3-U Q3, Q6, Q7, Oil
9 S3 AU-Z Ql, Q2, 03, 06, 07,
08, 09, 010
Reset of the ones counting logic is similar to the coarse and tens counting
logic reset. An output on the ones selector switch wiper occurs when all
inputs to the selected gate are "l". Reset of the counters is then provided
by double inverting this output and connecting it back to the counter reset
inputs. In this case the ones wiper is connected to the input of inverting
gate A3-H on board S15« Gate A3-P then reinverts this signal and provides
recet to SI and C2 Pins k, 8, 12, 16, L, R, V, and Z. The ones output at
the selector sv."itch is susimed with the tens and coarse counting logic output
in the counter output logic.
14-86
-------
Counter Output
The. counter output logic serves to sum the coarse, tens and ones counting
logic outputs toccther. The result of this summing is the total count per
revolution as dictated by the selector switches. The technique used is a
two level "OR" circuit. The tens and ones counting output are first inverted
then "ORcd" together. The "OR" output then goes to two additional "OR"
circuits where it is "ORed" with either the 7-13.5u. coarse or 3-5«5n coarse
counting logic output to form the total sum count. All the counter output
logic is preformed by the quad dual gates on board Sl*u The tens count
selector wiper is connected to an inverter gate Al-8 on SlU while the ones
wiper is connected to inverter gate Al-J. The inverted tens and ones are
then inputs to gate M-C and Al-3 respectively. The outputs of gates Al-3
and Al-C are tied together to form a wired "OR". Pins 3 or C of Slh would
then have the sum of the tens and ones counting logic output. The sura is then
inverted by gates A2-5 and A3-Z.
The 7-13.5ji coarse counting output is inverted by gate A3-22 of SlU and
the inverted counter is connected to the input of gate A3-V. A3-V is one
gate cf a wired "OR". The other gate is A3-17 which has as its input the
sum of tens and ones from gate A3-Z. The resultant output on Pins 17 and V
is the total count of 7-13.5^ coarse, tens, and ones counting logic. The
3-5.5u coarse counting output is inverted by gate A2-15 and provides input
to gate AZ-L, which is one half of an "OR". The other gate of the "OR" is
gate A2-10 which has the summed tens and ones from gate A2-5 for its input.
Pins 10 ajid L of SlU then are the total sun of 3-5.5n coarse, tens, and ones
co-anting logic. The two combined outputs at Sl'4 Pin 10 and 31*4- Pin 17 are
connected to the band selector switch on the control panel. The wiper of this
switch will then connect the appropriate cotmt to the direction sensing logic
through inverting gate Al-C on board S22. The total count will then be
steered to the (X) or (Y) input of the bidirectional counter by the direction
sensing logic.
Resolution Selector Logic
The output of the logic to the bidirectional counter is a pulse every 0.1 vave-
numbers. In many cases it is desired to take data at intervals other than
O.lcnr1. The resolution selector logic enables the operator to acquire data
at 0.1, 0.2, 0.3, 0.5, 1 and 2cm-1 intervals. To accomplish this the count-
ing logic output is fed into another counting circuit which is controlled by
a raultiposition switch on the control panel. The output of the resolution
selector logic is the input to the data control logic which is used to command
the data acquisition subsystem to take data. Components of the resolution
selector logic are a 528T counter on board S10, 502T quad dual gates on board
S13, 501T inverter on board S15, and a 502 gate used as an inverter on board
S22.
U-87
-------
It is desired to take data only when the monochromator is scanning in
one direction to avoid backlash problems. The direction of increasing
wavenumber was selected and hence, the (X) input to the counter is used as
the signal source. Counter (X) input on board S22 Pin 3 is inverted by
gate Al-J or S22 and connected to the counter input, board S10 Pin C. This
signal is also inverted by gate A3-22 on SI 3 and is connected to the resolu-
tion selector switch as the 0.1 cm"1 signal. Gates on S13 also sum the
various outputs of the S10 counter to form the other resolution elements. The
table below summarizes the resolution elements, their associated summing
gates, and counter inputs to the gates.
Resolution Element Summing Gate Counter
Cm"1 Board Location Gate Inputs
0.1 S13 A3-22 QO
0.2 S13 A3-Z Ql
0.3 S13 A2-L Ql, Q2
0.5 S13 A2-10 Ql, Q3
i'0 S13 A2-15 02, QU
2-0 S13 A2-5 03, 05
The signal on the wiper of the resolution selector switch is connected
to inverting gate Al-C on S15. Output from gate Al-C is reinverted by gate
Al-E and serves as the reset for counter S10. Pins k, 8, 12, 16, L, R, V}
and Z the reset lines for S10 are connected to SI5 Pin E causing the counter
to reset with each output.
Data Control Logic
The inverted resolution selector output at S15 Pin C is also connected to
the input of a monostable multivibrator at S2k Pin F. The purpose of this
monostablc ij to provide sufficient pulse width, amplitude and drive cap-
ability to start the data acquisition cycle. Figure ^.3.U.1 shows the data
control monostable schematic and drawing 596-722-031 may be referred to for
a schematic and component layout of this GD/C designed circuit. The data
control monostable utilizes the integrated circuit MC851 at the left in the
draw-big. Two other monostables (at the center and at the right in the drawing)
are used by the direction sensing logic.
-------
Figure U.3.U.1 Data Control Monostable
Output of the monostable is a pulse k.5 microseconds v/ide and h volts in
amplitude at S2k Pin H. Reference to the drawing shows that the actual
output at Pin H is from a Darlington amplifier. The requirement that the
data coupler input be terminated by 50 ohms necessitated the Darlington
amplifier on the monostable output. S2h Pin H is connected to the data con-
trol BNC connector on the control panel and from there drives the start
command input to the data coupler. Figure U.30^.2 is an interconnection
diagram of the data control logic to the system.
S15
S2U
J102 P102
I
c
Res. Sel. Input
Gnd Buss
F
H
B
nverter Data Control
Monostable
25
25
Logic
Box
BNC BNC (
x- -»
1 1
v. .J
Data Control Read 50
Output Command LO
n
ad
Cc
'J7)
Date
upl
Figure U.3.U.2. Interconnection of Data Control
The wiring table provided with tliis document ulso contains this information
and may be used for interconnection of cabling during set-up.
-------
U.3«5 Data Acquisition Subsystem
The data acquisition subsystem and its various components relationship to the
system is explained in the systems design section of this document. All of
the components of the data acquisition system with the exception of the analog
ratio module are vendor supplied equipment. Vendor supplied manuals for the
components of the data acquisition subsystem will serve as the source of
details on these components. The details section of this document will be
limited to modifications and interconnections of the vendor supplied components
and a complete description of the ratio module.
Wavenumber Conversion (Bi-directional Counter)
Conversion of the output of the wavenumber logic to wavenumber and then to a
BCD format is done by an Anadex Bi-directional Counter. Part number for the
counter is CB600R W/BZ, BL, G-4A, A. CBoOOR is the basic part number. W/
means with the following options: BZ preset zero capability, BL preset count
level, G-^A BCD printer output and A which is storage of count to enable "read-
out on the fly". Option A for this instrument was implemented after delivery
and is not reflected in the instrument manual title, but is included in the
text. The modification to the counter involved in this late change included
the factory addition of Option A and the addition of a control line to provide
a hold signal to Pin 9 of J6 anytime the data acquisition system was busy.
The hold signal is generated in the data coupler. Interconnection of the
counter to the system is shown in Figure U.3»5»l«
Log:
X
Y
BNC
BNC
X
Y
LC Box Connec
Feed T
Panel
BNC
BNC
tor
hru
X
Y
J5
J6
Counter
P5
P6
I
=J
>3
Da
J3
ta Couple
Figure U.3»5»l. Bi-Directional Counter Interconnections
14-90
-------
Source Digital Output Conversion (DVM 5^03-015)
Conversion of the source compensation amplifier output from an analog voltage
of zero to 10 VDC to a BCD format suitable for printing and recording on
digital tape is done by a Dana Model 5^03-015 DVM. This particular DVM has
a high speed sample hold plug-in Model 015 for its front end. This enables
the voltage reading to correlate exactly in time with the corresponding wave-
number. The sole modification of this DVM is the method used to input the
read command. Ordinarily the read input would be at the banana jacks on the
front panel. However, it was useful in this system to have a gate in the
data-coupler provide the read command, and it is connected into the DVM with
the rest of the control functions through P2C&. In effect the front panel
banana jacks arc now in parallel v/ith Pins 11 and 13 on rear connector J20J4.
Two additional wires in the output cable carry these linen to Pins '18 and ^9
on Jl of the data coupler. In turn, Pins hQ and U9 are connected through an
emitter follower and A5-1) to gate A 5 Pin ]2. This is the inverted data control
signal "anded" with the hold signal from Al-U via Al-3^. The effect is to
inhibit a read command to the DVM while the data acquisition system is still
putting out the previous data. The changes are documented in the data coupler
mar.ur.l. Figure U.3.5.2 gives the interconnections of the sample hold DVM to
the system.
Jl PI
P202 J202
P20k
BNC
Source
Cornp. Amp
Output
Data Coupler
DVM 5^03-015
Control Panel
Figure ^.3.5.2 Sample Hold DVM 5^03-015 Interconnections
I*-91
-------
Transmission Coefficient (f)-DJGital Output Conversion (DVM 5^03-010)
Transmission coefficient in a digital form is provided by a Dana Model 5*103-
010 DVM. This DVM is a 5^03 type with a -010 ratio input module. The input
signals are the source and reference compensation amplifier outputs. The
source compensation amplifier is connected to the input on the front panel.
Reference compensation amplifier output is connected to the DVM reference
input on the rear panel. The DVM is operated in the 10 times ratio mode
resulting in an output that is 10 times the transmission coefficient. No
modifications have been made to this instrument, therefore the manuals pro-
vided by Dana are completely correct. The interconnection of this DVM to the
system are shown in Figure U.3.5.3.
J2 P2
P202 J202
Data Coupler
Source Cornp.
Amp. Output
DVM ';'-103-010
Ref. Comp.
Amp. Output
Connector Control P/uiel
Feed Thru Pa.n^l
Figure U.3.5.3. Ratio DVM 5^03-010 Interconnections
14-92
-------
Analog Ratio Module
A strip chart presentation of the transmission coefficient requires an analog
signal representation of (T). This signal is generated by the analog ratio
module. Inputs to the ratio module are the source and reference compensation
amplifier outputs. The output of the ratio module goes to one position of the
strip chart input selector switch. From here (T), source^, or reference may be
selected for display on the strip chart. Figure H.3.5.1* is a schematic of
the ratio module referenced in the discussion. Drawing 596-722-030 gives a
schematic as well as component layout of the ratio module.
J*34
v<
•»«* «I.!DI "?
NvT—l T «" L
Tl\ ICOK
WlVt S>*-»=r:T —* •*+""
JXB
Figure U.S.5.U. I/I Ratio Module
U-93
-------
Central to the ratio module is the integrated circuit MC1595 which is a
Motorola linear multiplier. The circuit is similar to one recommended by Motorola
to produce a division of input signals. Exceptions to the circuit recommended
in Motorola application notes were made to improve the performance. Zener
diodes Dl and D2 were placed across the input to protect the circuit from exces-
sive input signal. Diodes D3 and DU were inserted in place of resistors. The
network R3, RU, R5, R6, D3 and DU is the input offset adjustment network. The
use of the diodes made possible a finer adjustment of the offset. Dual opera-
tional amplifier uA7^7 was used instead of the recommended Mstorola operational
amplifier to save components. Both amplifiers are similar but the MA7^7 does
not require external compensation and is used for this reason. A detailed
description of circuit operation is given in 1-fotorola application note AN-U90.
A brief description is given here to convey a general understanding. The MC1595
integrated circuit consists primarily of three differential amplifiers. There
are two differential amplifiers for the input amplifiers, Pin U(+) and 8(-) are
the inputs to one and 9^+) and 12( -) are the other inputs. The third differential
amplifier serves as the load for the amplifier with Pins 9 and 12 inputs. The
load differential amplifier is base driven by the input differential amplifier
with inputs U and 8. The output of the load differential amplifier is therefore
a function of the two differential inputs. In fact, the output is the product
of the two inputs. The divide circuit is siinply an inverting amplifier with
the product function in the feedback circuit. In this case the (l/2)p, A?Uy
with Pin 10 output is the inverting amplifier. The MC1595 and the other (l/2)vi
A?^7 form the product of IQ and I and make up the feedback component of the
inverting amplifier. Figure H.3.5.5 is a block diagram of the I/I ratio module.
o vw
i
KI V .
o out
MC1595
i
out
-O V
out
Figure U.3.5.5. I/IO Block Diagram
-------
From this simplified drawing it is easier to see the divider as a simple
inverting amplifier. The virtual ground at the (-) input makes the current
i and i equal to
KI V
o out
R
-I
R_
Assuming the "bias current i^ equo.u xcro and solving for Vout yif.j/1;
-IK.
out
o 2
If
V x = -I/I
out ' o
The divider circuit used has ^ equal to 100K and R^ equal to j.OX. K which
is adjustable is set for 1/10 generating the proper valus of VQut>, There .ire
four adjustments associated with this circuit. They are IQ offset (3~). I
offset (Rig), output offset (R^) ar.d the scale factor K(RP1) , Ths adjustment
procedure should not be required under normal conditions but 1." grvsr. here foi-
reference.
I/I
o
1.
2.
U.
5.
6.
Adjustment Procedure
Set I
Adjust R10/ for I/I0
Adjust RL for I/I
H ' o
Set I
Adjust FU for I/I
-J ' O
Adjust R21 for I/IO
K 0
= Constant for anv I
= 0V
= Xo
= Constant for e.ny I
= l.OOY
U-95
-------
Interconnection of the T/I ratio module and the recorder input switch
o
to the system is illustrated in Figure U.3.5.6.
S25
A
B
Recorder
BI
ntr<
P5
vc c
NC
3l 1
P3
*n
JU
Pi
Ol
Pan
L19
3l
J3
19
BNC
BNC /
I
s Recorder
Select
Switch
-^
0
0
I
T/T
I/Zo
Ratio
Module
I/I
?'•
??
10
OK
$J
?P
).<7
47
Gn
+21
-2
->
>
PI
d
4V
uv
17
ft
p
ji:
A
r
L7
Source
Lock- In
Amplif .
3 3
6 6
I
Connector
Figure U.3.5.6. I/I and Recorder Select Switch Interconnections
Digital Data Coupler
The purpose of the data coupler is to format the 13 BCD cliaracters output ted
by the counter and DVMs and, on command, cause them to be recorded on the
digital printer and/or the digital tape recorder. A Zentel Model 6^9 coupler
is used in this system. The manual provided by Zentel has a number of errors
and GD/C lias modified the instrument to a limited degree. Overall interaction
of this instrument with the cystem is described in the design section. This
I*-96
-------
section discusses the modifications, physical interconnection of the coupler
and the errors in the manual. Manual errors are listed here in the sequence
they appear in the manual.
1. Page U - First Sentence - this input must be driven from a low
impedance source as a 50 ohm termination is required at this input.
2. Drawing No. 9706-02 XFR, MODE & RS CLK labels at input to shift
registers in wrong place; corrected drawing.
Output of DG-3 is pin 22 not 23.
Operate and Standby labels reversed on S3.
3. Drawing No. 9076-OU; 2 of 2. P6 Pin 9 called follow is really the
counter hold line.
U. Drawing No. 90?6-05; 2 of 2 - Pins U8 and U9 of PI are the hold
command to the sample hold DVM 5^03-015.
5. P2 of the coupler is the input connector from DVM 5^03-010. No
drawing is given for this cable, however it is a duplicate of PI
except Pins U8 and U9 are not connected.
Modifications to the coupler system are pencil sketched on Drawing
9076-02. The manual start input circuit has been changed from a direct
switch to ground at AU-26 to a switch to +5 volts that is inverted by gate
A7-8. This avoids contact bounce double triggering the Start Flip-Flop.
The remote start which is the data control input originally was inverted
by gate A5-12 and inputted to the Start Flip-Flop. A modification "ANDS"
the hold signal through delay generator, DGU, with the remote start at gate
A5-12. The purpose of this change was to inhibit a second start or data
control pulse while the data coupler is still executing the previous command.
The third modification to the coupler provided a method of generating a hold
command to the bi-directional counter. Gates Al-U, Al-8, A5-9, and A5-33
are used in this modification. The output is "l" between the receipt of a
start command and the completion of execution of a data recording sequence.
-------
Gate Al-k inverts this "0" and provides a "1" to Pin 9 of P6 on the counter
which holds the counter output during the recording sequence. Use of the
pencil corrected schematic diagram Drawing 9076-02 and the timing sequence,
Figure 2 of the Coupler Manual, can be made to justify these statements.
Figure ^.3.5.? is an interconnecting diagram for the coupler to the system.
(J202) (P202)
Sample &
Hold DVM
(J20'4
1
5 103-01.;
(J20
Ra t i o T)VM
(J20^
5'403-010
(no
Counter
)
2)
\
)
I)
IF
(
-u
(]
— ! (p
,A
2014) >
J
P202)
N (P;
1
V.
20 U) /*
J
'
P101)
""1
-------
Automatic Marker-Analog Recorder
It is operationally convenient to have an automated marker system to
place wavenumber marks at the edge of the analog record. This allows the
operator to concentrate on more important aspects of the run.
The automatic markers system is driven by the decade units of the bi-
direction counter. Each counter decade has a previously unused output X'HIRO
which goes low when the decade reads zero (pin 26). A ground connection and.
pin 26 of the three least significant decades were brought out to Jll8 on the
back of the counter.
The counter information is conducted to the marker selector box located
just to the left of the analog recorder. There it is applied to simple logic
to produce a high output whenever the counter reads even units, tens or
hundreds of wavenurnbers. Since the logic units cannot drive the marker directly,
a driver consisting of two emitter followers and an SCR are used. A capacitor
on the output of the first emitter follower provides pulse stretching required
at the highest scan speed.
Power for the logic and driver is derived from +2'+ volts from the NIM BIN
via J120 by means of a zener diode.
Output of the marker selector goes to the right, marker jack at the rear
of the analog recorder.
Provision is made for selection of automatic, manual or no marker.
Manual marker input is on the front panel at the left of the analog recorder.
The automatic marker is shown on drawing 596-722-035 and in Figure U.3.5-8-
U-99
-------
p.jh
7 «••••
iOCJf-lfl
Figure U.3.5.8 Marker Control
U-100
-------
U.3.6 Data Recording Subsystem
The data recording subsystem consists of a strip chart recorder HP7701A with
its associated preamplifier KP8801A as an analog recorder, and two digital
recorders, a HP5050B digital line printer and a Kennedy l600H digital incre-
mental tape recorder. The system design section discusses their operation in
this system. Manuals have been provided by the manufacturer on each of these
items. No modifications have been made to any of this vendor equipment and
hence, the manuals can be directly referred to for detail information. The
interconnection of the digital recorders is shown in Figure U.S.5.7, the data
coupler interconnection diagram. An interconnection diagram for the strip
chart recorder is shown in Figure U.3.6.1.
Monochromator
Controller
I
P13 J13
AC
ACC J
AC }
A
B
C
E
A
B
C
E
Strip
Chart
Analog
Recorder
Righ
Mark
A
B
C
t
er_
P119 J119
A
B
C
it
A
B
C
3
6
3
6
2 Id
Wiper 2(+)
Wiper 1 (-)
Recorder
Input
Selector
Switch
P120 J120
J110 Fl-
Counter
A A
B* B
l
C C
1
D D.
1
L° Gnd
1'a
10 's
100 ' s
Marker
Selector
Gnd
•H2UV
A
B
A
B
Lock In
Man.
Input
Figure U.3.6.1. Strip Chart Recorder Interconnections
The strip chart motor may be run remotely. Normal operation of the
ROSE system has the strip chart in the REMOTE run mode. When the X DRIVE
switch on the raonochromator controller is turned on, both the monochromator
and strip chart drive motors are started. When the CHART switch on the mono-
chromator controller is turned on, the strip chart drive motor will run (if
the recorder is in REMOTE) but the wavenumber drive motor will not run.
U-101
-------
U.3.7 Electronics Calibration
Standardized signals are provided to enable a check of amplifier response
and data acquisition system accuracy. When the STD SIGNAL-OPERATE switch
is in the STD SIGNAL position a voltage of known amplitude is inserted into
the selective amplifiers. The ratio of the voltage inserted in the source
selective amplifier to the voltage inserted into the reference selective
amplifier may be controlled by a control panel potentiometer labled
"Standard Signal (T) Adjust".
Standard Signal Generators
A circuit called standard signal generator located at S20 of the logic box
generates the standard signal. Figure U.3.7.1 is a schematic of the standard
signal generator.
Figure h.3.7.1. Standard Signal Generator
-------
Drawing 596-722-025 contains both a schematic and a component layout of
the standard signal generator. This circuit takes advantage of the fact
that the output of the synch amplifiers is a signal which is frequency locked
to the source and reference choppers. Use of this signal as an input to the
standard signal generator ensures a calibration output signal at the chopper
frequencies. Both circuits are identical with the exception that their outputs
are mixed together differently. The amplifiers take an input signal that is
generally a ±15 volt square wave and attempt to provide a gain of 100. Output
will then be ±15 volt square waves at Pin 10 even, if the synch amplifiers are
not saturated. Diodes Dl, D2, D3, an?. DU are 6.U volt Zener reference diodes
each of which has an opposing diode in series with the Zener element. The
output to the resistor network is a ±6.U volt square wave independent of input
signal condition and amplifier characteristics. Voltage divider R9, RIO, Rll
results in a 1000 to 1 division of its input voltages at S20 Pin U and S20 Pin
J appearing at S20 Pin P. If the STD. Signal (T) Adjust potentiometer is set
nearest Pin D, equivalent to (T) equals 1.0,both inputs at Pins U and J are 6.U
volts. The output called "Cal Signal" is then a mixed signal of 6.U mv of each
of the chopper frequencies. Since the (T) adjust potentiometer is connected to
t?m source standard signal it controls the percentage of source signal mixed.
This is equivalent to it being a linear control of (T) provided by the standard
signal generator. The wiring table presents clear and concise interconnection
information for this circuit which is completely hard wired.
U.3.8 Power Subsystem
i'he 115V 60 Hz input power to the instrument is converted internally to D.C.
voltage, blackbody heater currents and chopper drive voltages. Again, detailed
information is contained here on the GD/C designs and references to vendor
manuals are made on vendor equipment.
D.C. Voltages
D.C. voltage requirements are ±2^, ±15, ±6 and +5. The ±24 VDC is supplied by
the PAR Model 200 NIM BIN. Its primary purpose is to supply the PAR amplifiers
plugged into it with ±2U VDC. However, it was decided to have the PAR pre-
amplifier located remotely near the detector. The ±2k VDC from the NIM BIN
was cabled to the receiver assembly stand for the preamplifier. The +2U VDC
available at the receiver assembly stand was also utilized for detector bias,
gyrator and source synch preamplifier supply voltage. Interconnection of the
±2k volt supply in the system is shown in Figure U.3.8.1.
U-103
-------
pn6
Source
Synch.
Preamp
U
6
U
6
J11'4
PAR 210
Preamplifier
Direct
Input
I
28 28
29 29
BNC
Stand
Panel
i
J113 P113 P115 J115
1^
A A
I
B B
I
C C
Gnd
Stand
Interface
Detector
5 -5
7 7
i
6 6
NIM BIN
Source Sel.
Amplifier
Source Lock-In
Amplifier
Ref. Sel.
Amplifier
Ref. Lock-In
Amplifier
Figure U.3.8.1. ±2k VDC Interconnections
The bias to the detector is simply a 10K ohm resistor tied through a
low pass filter to the ±2k VDC fed through the input cable.
A Data Technology Model 597 modular power supply is used to provide ±15V
and + 5 volts D.C. This multiple output power supply is located in the logic
box. The predominate usage of ±15 VDC is by the I.C. amplifiers used in such
circuits as the synch, compensation and voltage follower amplifiers and the
standard signal generators. All of these circuits are in the logic box.
Digital integrated circuits use +5 VDC; the power supply and the circuits
which use this voltage are located together .in the logic box. Complete infor-
mation on this power supply is contained in the Data Technology specification
manual. Circuits providing ±6 VDC located in the logic box at Sl6 and S17
are used primarily as the supplies for the encoder. They are however also
used to supply bias for the LED and diode detector associated with the genera-
tion of the reference synch signal. Figure U.3.8.2 is a schematic of the
±6v power supplies. Drawing 596-722-028 contains this schematic and a com-
ponent layout for the ±6 VDC supplies. The two supplies have closely
corresponding test points and pin numbers with the positive supply being at
Sl6 and the negative at S17.
U-10H
-------
Figure U.S.8.2. ±6 Volt Power Supplies
Both power supplies are sinu lar in that they both utilize a 10 volt
secondary of a transformer for the unregulated input and a Fairchild
as the regulator. The negative regulator is a standard configuration for
the use of a nA723 as a negative regulator. Output voltage from this con
figuration is determined from the formula
-V
V
out
ref
2
R + R
_3
R,
-------
where
Ri
V = 7.15 VDC nominal
ref
. v 2.U3 + 3.57
out 2 /x 3.57
3.57 XTT^ = -6 VDC
Diode Dl is a 6 volt Zener diode used to make Pin 10, the output of the
regulator, run near ground. Ql a 2N2905 PNP transistor acts as the pass
transistor in this series regulator minimizing the current drained directly
from the regulator. The positive voltage regulator must provide significantly
more current than the negative supply. For this reason CU is much larger
than Cl. Also, the high output current requirement is reflected in the use
of the 2NU2UO for the external pass transistor. This is a power transistor
located on a heat sink next to the transformer. Resistors R6 and R7 are the
output voltage determining components where the output voltage is determined
V = V " R7
out ref R6 + R7
V = +6 VDC
out
Resistor R8 is a current limiting resistor. When th- voltage across R8
reaches 0.6 VDC it turns on a currenting limiting trcnsistor inside the I.C.
and removes the drive to the pass transistor. In this case R8 limits the
output current to 600 ina. Interconnection of the ±6 VDC to the encoder and
synch pulse generator is sufficiently clear in the wiring tables. To trace
the interconnections start with Sl6 and S17 Pin A for the -i6v and -6V
.-respectively.
U-106
-------
Chopper Drive
The source chopper is an. Electro-Optical Industries Model 3^-1 mounted on the
source blackbody. The control unit that allows for selection of the chopper
frequency is located in tho source auxiliary stand. The relationship of the
chopper to the system and its justification are covered in the system design
section. A vendor manual on the Model 311 is provided and sufficiently
covers the chopper and its drive circuitry.
The reference chopper and its associated drive circuitry are a GD/C design.
Mechanical and optical considerations are covered in their respective sections
as this component is predominantly mechanical and optical in nature. This
section describes the drive circuitry and interconnection of the reference
chopper. The reference chopper motor (Globe Industries 83A/008) requires
115 VAC, kOO Hz and kO watts nominal. Since the motor is an A.C. hyteresis
synchronous type its running speed is set by the drive frequency. Nominal
frequency used in this system is kkO Hz which yields a chopping frequency of
330 Hz. This frequency is adjustable over a minimum ±10% of the center fre-
quency. This ensures that the operating frequency will not be a harmonic of
either 60 Hz or the source chopping frequency. Figure U.3»8«3 is a schematic
diagram of the circuit called the chopper motor drive. This circuit i« in a
chassis located in a portion of the strip chart recorder rack not used by the
recorder. The reference chopper drive is shown on drawing 596-722-029.
Figure U.3.8.3. Reference Chopper Motor Drive
Input pov/er to circuit is 115V 60 Hz. It is rectified by a modular full
wave bridge Motorola MDA-962-Z and capacitor Cl.
-------
Output of the bridge is 165 VDC . The A.C, input is controlled "by the reference
oscillator on-off switch located on the control panel. When the switch is
in the "on" position the D.C. supply voltage is divided by capacitors C2
and C3 and can be looked at like a isupply for the power amplifier portion
of the circuit. D.C. input voltage is also zenered to +Ik VDC by diode D5
and resistor R3. Fourteen volts then becomes the supply voltage for the
oscillator portion of the circuit„ Ql and Q2 are 2NU871 unijunctions serving
as the active components in a unijunction relaxation oscillator. Frequency
determining components are C8, R6, R9 and R7. Frequency adjustment is made
by the 2K ohm potentiometer R?. Diodes D3 and DU serve as flyback diodes to
prevent damage to the 2H^8?1 unijunction. Transformers Tl and T2 (Sprague
11Z12) couple a pulse form of the oscillator output to the gates of SCR1
and SCR2. Capacitor C5 with either LI or L2 is a series resonant circuit.
The result of alternately switching the opposing voltage on C2 and C3 into the
resonant circuit is a sinusoidal output of 115 VAC at the oscillator fre-
quency. Diodes Dl and D2 in parallel with the SCRs are to prevent the
resonant circuit from presenting large reverse voltages across the SCRs.
Network Rl, C6 or R2 C7 aid the turn on characteristics of the SCR's. Experi-
ence with this circuit indicates that if something causes the circuit to fail
the 2KU'^3 SCRs will invariably short anode to cathode. Thus they should be
checked first in a trouble shooting procedure,
Figure U.3.8.U is an interconnection diagram of the reference chopper
drive circuit.
Logic Chassis Control Panel
TE1-1
PI
AC Line
AC In
Chopper
Drive
TB2
f.
•7
' I
D7 ' J107 J102 P102
1
A A
R R
H-
»
Monochro.
Controller
29
30
29
30
AC Line
On
Off
\"
> Ref . Osc.
TB2 P105 J105
6
7
1
9 9
10 10
1
1!
1"
Jl.
LO
C
A
B
P110 VJht/Blu
C
A
B
^ Blk
C Red
1 Brn
Stand
0
o
a
~3\
$
Chopper
MO to r
Figure U.3.8.U. Chopper Motor Di'ive Interconnections
U-108
-------
Elackbody Heaters
The two blackbody controllers are identical Electro-Optical Industries
Model 2l6A temperature controllers. Their basic principle of operation is
explained in the desicn section and their details are adequately covered by
the vendor supplied manuals. Therefore, further discussion is not necessary
in this section.
-------
5.0 SYSTEM OPERATION
In this section information relating to system operation is given which in-
cludes preliminary calibration, system installation, starting t.ie system,
test parameter selection, procedure, and system shut-down.
Prior to operation, the equipment manuals should be read carefully. The
instructions here are intended to augment those of the manuals particularly
for conditions which are unique for the ROSE system.
5.1 PRELIMINARY CALIBRATIONS
There are a number of preliminary calibrations which should be made. Mor.t.
will need to be made infrequently as indicated in the following sections.
5.1.1 Blackbody Calibration
After each rebuilding of either blackbody, or at other times if there is
sufficient reason, it will be necessary to determine the control settings which
will produce a match of the source and reference blackbody temperatures. An
opitcal pyrometer is almost essential to this operation (although the radio-
meter probe could also be used it does not give a direct temperature readout
but only indicates equality of radiance). The procedure given in Section
U.I.I should be followed.
5.1.2 Electronic Calibration
It is assumed that checkout of the electronic components recommended by the
manufacturers in the instrument manuals will be carried out as required. Be-
yond these checkouts it may be desirable, from time to time, to check
particularly the system gain.
A 18 millivolt peak-to-peak square wave calibrating signal is available
at the lock in amplifier REFERENCE IN/OUT connector when the reference switch
is in the CAL position. In the ROSE system a calibration in terms of lock-
in amplifier D.C. volts out per rms volts input is desired. This kind of
calibration is described in the lock-in amplifier manual; the calibration is
applied to the INPUT of a selective amplifier whose RESONANCE OUTPUT is
connected to the INPUT of the lock-in amplifier. For the original lock-in
instrumentation the least sensitive 10 mv range was used (sensitivity ranges
are 1, 25 and 10 mv) and, with a Nfodel 210 selective amplifier gain of 1.0,
the lock-in meter is set to 0.8l of full scale by means of the GAIN ADJ. on
the lock-in amplifier front panel. The ratio of the peak to peak voltage of
a square wave to the rms voltage of the fundamental is 2.22 so that the rms
5-1
-------
fundamental output voltage of the- scO.active amplifier in this case is 18/2.22 = 8.1
millivolts. By setting the meter to 0.8l of full scale on the 10 millivolt
range the instrument MONITOR output is calibrated to read 10 volts D.C. out for
10 miU.ivolts rras fundamental input (meter full scale equals 10 volts D.C. at
the MONITOR output). This can be looked upon as a lock in amplifier gain of
1000 volts DC/volt rms from the selective amplifier INPUT to the lock in
amplifier MONITOR output.
The Model 220A lock-in amplifier has been modified to have 100 times less
sensitivity or gain. It is stated in the lock-in manual revision that the CAL
output, therefore, cannot be used (it is still 18 mv peak to peak). However,
if the 220A lock-in amplifier is placed on its most sensitive range of 100 w
and a GAIN setting of 10 is used in the selective amplifier the overall sensi-
tivity is again 10 mv and the original procedure of applying the calibration
signal to the selective amplifier INPUT and setting the meter to 0.8l of full
scale as before may be used. The overall gain can be looked upon as a gain of
(10 volts DC lock-in amplifier output)/(10 millivolts rms fundamental input) or
an overall gain of 1000 volts DC/volt rms. With a GAIN setting of 10 in the
selective amplifier in this case, this overall gain corresponds to a gain of
100 volts DC/volt rms in the lock-in amplifier in the mast sensitive position.
A new GAIN label on each 220A lock-in amplifier is marked 100,50,20,10 to
correspond to 100,200,500, and 1000 millivolt SENSITIVITY settings of the
modified lock-in amplifier. These lock-in amplifiers GAIN settings refer to
the DC volts at the MONITOR output per rms volt at the lock-in amplifier INPUT.
Calibration can be extended to include the Model 213 preamplifier by
using an appropriate precision voltage divider between the calibration signal
at the REFERENCE IN/OUT terminal of the lock-in amplifier and the INPUT terminal
of the Model 213 preamplifier.
The gain of the source voltage follower and the source compensation
amplifier may be checked by using the D.C. output with ZERO SUPFR. on the
lock-in amplifier as a signal source (connect the lock in MONITOR output to
the SOURCE LOCK IN INPUT terminal on the control panel) and reading, by
means of the DVM, the voltage there and at the SOURCE COMP. AMP OUTPUT
terminal with T SIG set at maximum (= 1,000). ZERO SUPP should not exceed
.125 (= 1.25 volts) since this will give 10 volts at the source compensation
amplifier output (gain = 8.0 nominal). Note that the SOURCE LOCK IN INPUT
is a misnomer since that terminal is actually the source compensation amplifier
input. A similar situation exists at the terminal labelled REF. LOCK IN
INPUT.
5-2
-------
The gain of the reference voltage follower and the reference compensation
amplifier can be checked in a similar manner with the following exceptions.
The SOURCE LOCK IN INPUT must be zero (a 5K resistor in a BNC connector at
this terminal is best; shorting may upset the bias). The polai-ity of the £KRO
SUPPR must be reversed and applied to the KEF LOCK IN INPUT terminal for a
positive reference compensation amplifier output. The maximum ZERO SUPPR In
this cace is -1.000 (= -10 volts) since the reference compensation amplifier
gain to the reference signal is nominally -1.0.
Be sure to return the ZERO SUPP selector switch to OFF before attempting
to use the lock-in amplifier for normal operation in the transmission mode.
5.1.3 Monochromator Calibrations
There are two types of calibrations which may be made, from time to time,
as experience indicates a need for them. These are slit calibrations (of
width and height) and wavenumber calibrations. Both of these have been made
and the procedure and results are given in Section U.l.U. Slit width and
height calibrations will probably need to be made infrequently. Unless there
is reason to suspect the wavenumber calibration, it will also need to be made
infrequently.
5.2 SYSTEM INSTALLATION
System installation consists of selection of a suitable site, setting up
and aligning the stands which includes making interconnections between the
various components.
5.2.1 Site Selection
The selection of a site will depend on many factors so that only general
guidelines can be given. Operational factors such as wind direction and back-
ground will be important in selecting a site for emission tests. Location of
the path for transmission tests will be governed by the availability of sites,
wind direction and the nature of the test object itself. The convenience of
commercial 110V 60 Hz power should be considered along with firm footing for
the stands and if possible a pleasant working environment. In almost all cases
the sites will be a result of compromise betwen the above and possibly other
factors.
5-3
-------
5.2.2 Stand Set Up
If the telescopes have been removed from the stands these shculd first
be assembled following the instructions given in Section U.2.5.
After placing the various main assemblies roughly in position the inter-
connections should be made. After a few set-ups these will become routine.
Intially, or after long periods, the following references will be helpful
(596-722-033 is the interconnection drawing).
Blackbodies 596-722-033 and Section 4.2.4
Cryocooler 596-722-033 and Section 4.2.10
Rcvr Stand Panel 596-722-033 and Section 4.2.1
Electronic Consoles 596-722-033 and Section 4.3
Power 596-722-033
With the connections made the stands are to be aligned.
In the emission mode of operation the objective is to point the receiver
stand assembly at a given target. The wide field alignment device is placed
in the holder at the monochromator entrance slit and after roughly pointing
the stand assembly in the desired direction and retracting the wheels the
object is brought to the center of the reticle field by successive approx-
imations. After the first approximation the sides of the front pads shoald
be aligned with the rear pad as shown on Figure 5.2.2.1 by sighting along the
sides of the front pads. Final azimuth and elevation adjustments can be
made as indicated in Section 4.2.1.
In the transmission mode of operation the objective is to point the
telescopes at one another. First, the stands should be roughly aligned by eye.
Then, using the wide field eyepieces, the azimuth and elevation adjustments
should be made by successive approximations to bring the image of the remote
telescope onto the center cross lines of the eyepiece reticle. The front
pads should be aligned as shown in Figure 5.2.2.1 Final azimuth and elevation
adjustments can be made as indicated in Section 4.2.1 using the microscope
alignment device.
Note that the field of view in the wide field alignment device is inverted
relative to that in the microscope alignment devices.
5-4
-------
k" Square
Front Pads
I»" Dia.
Bottom Plate
Rear Pad
Figure 5.2.2.1 Stand Pad Alignment
5-5
-------
5.3 STARTING THE SYSTEM
After setting up the system and making the interconnections as described
in Section 5.2, the next step is to start up the system. There is a preferred
order based mainly on the equipment warm up times. A typical starting schedule
as shown on Figure 5.3.1 which is intended as a guide. Experience may indicate
desirable modifications of this schedule.
Following the schedule are detailed discussions of starting procedures for
several components. The equipment manuals should also be consixlted for more
component detail. The procedures given here should be sufficient for normal
operation and include those particular to the ROSE system.
Entries in the various log books are considered very important in order
that variations in equipment performance may be determined aJid appropriate
action taken, if necessary.
After making the preparations described in this section the system is
ready for operation.
5.3.1. Blackbodies
The blackbodies have the longest warm-up time and should, therefore, be
started first. After turning on the blackbody cooler and checking to be sure
the glycol coolant is circulating, set the blackbody temperature controller
to HI range and 500 on the dial (1000 full scale) and turn on the controller.
After 90 minutes turn the dail to 600. After 5 minutes turn the dial to 800.
After 5 minutes turn the dial to 900. After 5 minutes turn the dial to the
setting corresponding to a temperature of 1800K. After 90 minutes the black-
bodies should be ready. Note and record the controller dial and meter readings
and the cavity sensor readings (on a DVM) in the BLACKBODY OPERATING LOG.
Comparison with previous readings is an indication of the operating condition.
A progressively increased meter reading over previous readings at the: loOOK
setting has sometimes been an indication of impending heater burnout.
5.3.2 Detector Cooler
After starting the blackbody cycle, begin evacuation of the Dewar with
the vacuum pump and observe the pressure indication of the thermocouple
vacuum gage on the receiver auxiliary stand. After the pressure has dropped
to below 50 microns, the detector cooler can be turned on; however, it is
best to let the pump lower the pressure as much as possible. Therefore, it is
recommended that the detector cooler be turned on about 30 minutes to an hour
before the cooled detector is actually needed. Note the time, the reading of
the detector cooler suction pressure and oil level (before and after turn-on)
in the DETECTOR COOLER OPERATING LOG.
5-6
-------
Time Item
t - 195 min. Blackbody Start (Dial 500) (cold start only)
t - 150 Start Dewar Evacuation
t - 105 Blackbody Dial = 600
t - 100 Blackbody Dial = 800
t - 95 Blackbody Dial = 900
t - 90 Blackbody Dial = (Setting for IfiOOK)
t - 60 Source Chopper On (transmisrixcn o
t - 60 Reference Chopper On
t - 30 Detector Cooler On
t - 30 Electronic Power On
t - 20 Dewar Vacuum Valve Closed (if P <
t - 15 Detector Cooler Temperature Set
t - 0 System Ready for Operation
Figure 5-3.1 Typical Starting Schedule
5-7
-------
Usually the first indication of cooling is a drop in the thermocouple
vacuum gage pressure reading which indicates cryogenic pumping. When this
occurs the vacuum valve on the dewar can be closed. The vacuum pump can be
turned off, if desired. The hydrogen vapor pressure thermometer on the dewar
will drop slowly at first and after 15 to 20 minutes or so will reach about
70 psia at which point it will drop quickly to near zero indicating a temperature
below the 26K operating point has been reached. Note the time and readings
in the DETECTOR COOLER OPERATING LOG.
Then turn on the detector cooler temperature control in the receiver auxiliary
stand using previous operating log readings as a guide. The TEMP, dial settings
are not calibrated but D300 to D^OO can be used as a start with the SENSITIVITY
dial set near zero. If the meter on the detector cooler controller does not go
up-scale increase the SENSITIVITY slightly (0.01 or so). The meter normally
oscillates for a few minutes during which time the hydrogen pressure rises
indicating that the heater is warming the cold head intermittently. If the
oscillations do not die out after several minutes decrease the SENSITIVITY
slightly; the setting seems to be rather critical. The hydrogen pressure
of 58 psia ± 1 psia corresponds to the normal cold head temperature of 26K ±
IK. Change the TEMP dials on the detector cooler temperature controller until
the desired temperature is obtained. Preliminary tests indicate any pressure
between 50 to 60 psia will be satisfactory. Perhaps even wider limits can be
used. After the temperature has stabilized record the time and readings in
the DETECTOR COOLER OPERATING LOG. The detector cooler is now ready for
operation.
5.3.3 Choppers
The choppers need to be turned on beforehand because of small drifts which
occur during warm-up. These drifts are greatest just after turn-on so that
after 15 to 30 minutes the choppers can be used if one is willing to tweak
the frequency controls of the selective amplifiers and lock-in amplifiers
and recheck the phase of the lock-in amplifier. However, for best results
the full warm-up time should be allowed.' The meter on the source chopper
should be set near 170 on the 300 range, which should give a source channel
frequency near 570 Hz. The frequency of the reference chopper should be about
330 Hz and normally does not need to be adjusted. With the 110V power applied
to the NIM BIN and the logic box and the SYNCH OUTPUT terminals on the control
panel connected to the REFERENCE IN/OUT terminals on the lock-in amplifiers
the synch signals may be observed on the lock-in amplifiers by setting the
METER/MDN. switch to REF. The meter reading is normally about 0.80 of full
scale with the normal setting of the REFERENCE LEVEL control on the lock-in
amplifier. Such a reading indicates that the choppers are working properly
and are ready for operation.
5-8
-------
5.U TEST PARAMETER SELECTION,
There are a number of paramatf..-^ which miist be selected in order to
operate the ROSE system. The basis .for selection of these parameters is discussed
in this section. A SYSTEM OPERATING LOG is provided in which these parameters
should be recorded; data is practically worthless if the parameters are not
known. Completion of the log will aid in discovering controls which are not
set in the proper position.
It will be convenient to assign run identification (I.D.) numbers by
means of which different records may be later identified and analyzed by
reference to the SYSTEM OPERATING LOG. Five digits can be recorded on the
digital recording system; a run I.D. number consisting_6f the month. day and
run sequence number has been used. For example, the second run on March 27
would have a run I.D. number of 32702. The date is still necessary to distinguish
between November and January or December and February and to record the year.
The parameter selections are grouped into spectral parameters, slit height and
width selection, tine constant-scan speed relations and consideration of
selective amplifier Q.
5.1+.1 Spectral Parameters
Spectral Region of Interest
The first parameter to be selected is the spectral region of interest.
This may be one entire band or only a small portion of a band of particular
interest. There are two wavelength bands which are designated (for identi-
fication) 3-5.5 microns and 7-13. 5 microns.
Electrical limit switches restrict the wavenumber regions from about
to 3830 cm"1 (7.1p to 2.6 microns) for the "3-5-5 micron" band (2hO L/mra) and
from about 590 to l6lO era"1 (16.8 to 6.2 microns) for the "7-13-5 micron" band
(101 L/mra). The useful wavenumber limits depend mainly on range because of
the absorption by normal atmospheric constituents.
The short wavelength cutoff filters restrict the wavelengths to approxi-
mately X>2.8 microns (»<36(X> cm"1) for the 3-5-5 micron band and to X>7.0
microns (^
-------
Grating
The 2hO L/mm grating is used for the 3-5.5 micron band and the 101 L/ram
grating is used for the 7-13.5 micron band. The selection is made by means
of a control on top of the monochromator (see Section 5.5.1).
Filter
Normally there is a short wavelength cutoff filter associated with each
grating. A 3 micron cutoff filter is used with the 2^0 L/mm grating for the
3-5.5 micron band and a 7 micron cutoff filter is used with the 101 L/mra grating
for the 7-13.5 micron band. However, there are occasions for which other
combinations may be used. For example, a higher order "HO band was used to
perform a wavenumber calibration and, in this case, no filter was used.
The filter selection is made by means of a knob (on top of the mono-
chromator) which controls a filter wheel. Positions for each spectral band
are labelled along with OPEN and SHUT positions of the filter wheel.
5.U.2 Slit Height
The slit height in the transmission made of operation should be varied
according to the range being normally set equal to the image height, h , as
indicated on Figure 3.3.2.7. Use of a smaller height cuts down signal; use of a
larger height adds no more signal but may reduce the noise from image move-
ment in the vertical direction resulting from atmospheric refraction. For very
short ranges, e.g. in the laboratory, a maximum slit height of about 8 mm
should be used (see Section S.U.I); for larger slit heights the ray boundary
envelope exceeds the blackbody cavity opening size.
The slit height in the emission mode of operation should be set equal to
12 mm if the object being observed is of sufficient size (see Figure 3.3.2.1).
This 12 ram height corresponds to the detector length of 2mm as imaged by the
6X detector optical system on the monochromator slits. The slit height may,
of course, be reduced to fit the object of interest but with a loss of signal.
5.I*.3 Slit Width
The slit width is probably the most important single test parameter because
of its large effect on other operating parameters.
The slit width chosen will depend on the type of test being run and the
character of the spectra being examined. It is convenient for functional
checking to use a standardized set of parameters. A slit width, s, of 700
microns is used for the 3-5.5 micron band and a slit width of 300 microns is
used for the 7-13.5 micron band. Variations of the signal obtained in these
5-10
-------
functional checks may indicate a need for realignment, re tun ing or other
action.
The maximum slit width is about 1200 microns which corresponds to the
200 micron detector image formed by the 6X detector optical system.
Under the conditions of laboratory or field operation that best slit width
will, almost always, bo determined empirically using several trial widths.
The choice will be Governed mainly by the signal available, noise and the
spectral line width and spacing in the spectra of interest or in spectra of
interfering gases. The discussion given below will help to choose the proper
slit width and shows its effect on the other operating. parameters of signal to
noise ratio, scan rate and time constant.
Single Line Signal
The instrument response to an isolated spectral line having an effective
or equivalent width, AM , which is about the same as the spectral slit width,
AM, is the convolution of the line shape and the slit function. The details
of the response depend on the details of both the line shape and the slit
function. The analysis of such an output and the "deconvolution" of the out-
put to obtain the line shape are too complex to discuss here in the time and
space available.
The area of an output transmission curve between the curve respresenting
the line response and the curve (or baseline) without the line is not dependent
on detailed Knowledge of either the line shape or the slit function. It is
sufficient for the present purposes to define the area referred to above in
terms of the line width and slit function width.
^.U.3.1 chows schematically the instrument response to a single
line. It might seem, at first, that &v should be made as small as possible to
increase the deflection for a given value of AM • It must be remembered,
however, that the curve shown is a relative transmission curve. The output
signal is the product of the transmission curve (T/T ) and the baseline or
background signal. For a continuum background this signal equals
J J 2
S = K 7 SAM- K 7 s (dM/ds)
B J. J J. J
o o
where K involves factors of radiance difference, Afys, transmission, modu-
lation factor, etc., s is the slit width and AM is the slit function width.
4t
Line shape as used here refers to the absorptivity or transmissivity vs
wavenumber curve.
5-11
-------
For an Absorbing Line
Av [l-(T--o) ] /"(i-T) dv
1.0
Lin-3
For tho SLit Function
1.0
T/T
0
A
v : Instrument; Wavenumber Getting
V-V
V.-v - 0
h o
/T\
i — I ft
IV
MIN
(I" =
°MIN
Av
L
V •- •> - O
':- o
Figure 5.1*.;5..L Gp-^^^al Line
5-12
-------
The factor (J/J ) is an irradianc?. ratio discussed later, ^ince
proportional to°s>the background, Sfi, is proportional to s .
The maximum height of the "line" output signal, S^, is
K -
K1J
o
Thus, S , depends on the first power of the slit width, s.
L
The factor (dv/ds) in the equation for S deserves some comment for the
case in which the slit width is comparable to the diffraction pattern half
width, a = XF/D. When the slits are wide, (s/a) » 1.0, the value of dX/ds
(or dv/ds) is essentially equal .to that calculated from the grating equation,
(dv/dx) (or (dA/dx)g; see Section 3-3.5. When (s/a) is comparable to 1.0
the image at the exit slit is spread out and the slope dv/ds decreases as
shown on Figure 5.U.3.2. These curves were calculated from the analysis
referred to in Section 3.3.5 for incoherent illumination of the entrance slit.
Although the coherence increases as the slit is closed such effects are not
considered here because the effects of the coherence change are relatively
unimportant to the main subject of slit width selection.
The equations for S and S also contain a term, (J/JQ)> which is of
importance when s is comparable to a. This term is the relative irradiance
at the center of the exit slit resulting from the spreading of the image by
diffraction. Figure 5.H.3.3 shows the relative irradiance as a function of
(s/a) calculated from the analysis of Section 3.3«5^
This factor is of importance only for values of (s/a) below about 2 or 3;
e.g., slit widths less than about 100 to 150 microns at X = 10 microns for the
present f/5 system.
5-13
-------
1.0
dv/ds
(dv/dx)
g
dv/d
(dv/dx)
d(F(s/a;
d(s/a)
1.0
2.0
(dv/dx)
2.0
t
>
1.0
0
1
i-
A
aa
-
j
3
•
j
»
f
"
j
&
/
*
f
V*
J
~^
^
f
s
j
f
^
/
t
-
j
jf
2
/
^
i
-
S
/
/
S
I
?
s'
a
-
j
f
f
s
A
/*_!
-
(
t
i
1
s
a
i
_
\
f
/
+ F
LJ '
f
/
f
,
(&\,
t
f
^
f
/
t
\
f
/
\
^
r
f
S
f
S
f
(dv/dx)
O
I
i
-
-
f
S
f
S
+
t
f
/
t
s
,
/
j
-
4
j
/
/
f
/
/
j
i
f
-
/
1
i_
i .
_u
..
1
-
-
!
1
~
:
l.Q 2.0
s/a
Figure 5.^.3.2 dv/dx vs. s/a
5-lU
-------
1.0
J = Irradiance at Image Center
J = Irradiance at Entrance Slit
o
s/a
Figure 5.^-3.3 Exit Slit Irradiance
5-15
-------
The instrument response to an isolated spectral line having an effective
width,Af . narrow compared to the slit function width,^, is a triangular
deviation from the baseline. The equations for S and S given before apply
here also.
Groups of Lines Signal
For a series of lines (AA «AA) spaced a spectral distance, d, apart
(which are not substantially overlapped) the height of the triangular response
is proportional to the slit width (through its effect on AO) so long as the
spectral slit width is less than (d/2) where d is the sp'ectral line spacing.
If the spectral slit width exceeds d/2 then there is a substantial reduction
in the spectral structure and the output takes on the appearance of a band. For
A v = m (d/2), where m is an even number, the spectral structure vanishes com-
pletely for a uniform spacing, d. Therefore, to get as much structured "signal"
as possible one should open the slits as wide as possible but not to exceed d/2.
One may consider for line structure the criterion:
AX < (d/2)p or £„ < (d/2) cm"
max max
For some spectra involving groups of lines it will be impossible to
satisfy the line spacing criterion because of the smallness of d. In this
case also, the signal S varies with sAi/ or s (dt//ds) as before but the band
signal from many lines having spacing, d, is
m r i
NL L U
O
where n = number of lines within the slit width Ai>
= Ay/dhas been included in the factor K.
Thus, the band signal for a given set of lines will increase with sA»>
s2 (di//ds) also.
5-16
-------
Signal to Noise
To determine the slit widths appropriate to various signal and noise
conditions consider the case in which the noise is not a function of the
signal, i.e., either detector noise limited or system noise limited.
S Signal _ (AN(y))(ACVs)Av(l-Qr)TM s
N = Noise
(Constants) D*VAA_ .
d r
d
For a line,
For a continuum baseline,
SB J J 2
~ = K2 — s *„ /T= K2 — s (di//ds)
o o
For a group of lines,
where K includes K and all of the factors in the noise except bandwidth, Af,
or what is equivalent, T, the system time constant. If the noise is independent
of the signal, these relations indicate that the longest available time constant
T, and the largest slit width, s, should be used (subject to (Ai/
-------
T « At (see Section
N « /Af « /I
T
= noise
Consider two operating conditions which are denoted by subscripts 1 and 2.
First, for isolated spectral lines, the ratio, H^ of tfce signal to noise ratios
may be written as follows.
I/ '2
(J/J
o'2 s2
(J/J^
(J/J0)g sg
(J/Jo)1 si
(dy/ds)
(dy/dt)
g gJ
1 slj
The scan rate ratio may be expressed:
(di//dt)
(di//ds)
For large slit widths (compared to a)
(dv/dt)
For the same
signal to noise ratio at the two test conditions, RL = 1.0,
5-18
-------
(
-------
For the baseline signal, S , or for the signal from a group of lines (or
a band), S , the signal to noise ratio may be written as follows for the two
cases as before.
2 /S2\2 (d"/dS)2 K
1 = (J/Jo}l VV ^/ds)l V Tx
B
(J/J0)2 /S22
(J/Jo}l
The scan rate ratio may be expressed:
= R
B
dy/ds)
lor large slit widths (compared to a)
(dv/dt)1
((s/a) » 1.0)
and for R = 1.0
B
; - («)
The time constant ratio may be written:
2
T rri/.i ^ 1
2 2
((s/a) » 1.0; R_ = 1.0)
D
(di//ds)
2
5-20
-------
For large slit widths (coapared to a)
and for R = 1.0
D
((s/a) » 1.0; R = 1.0)
An example of the ratios of scan rate and time constant is given in the
table below for a ratio of (sl/s2) = 2 as before (Rfi » 1.0).
(dv/dt)1 Tg
sl/a s2/a (dv/dt)2 ^
12 6 32 16
21 6? 29
1 0.5 580 135
Thus, large reductions in scanning speed and increases in time constant
are required to maintain signal to noise ratios for slit widths comparable to
the diffraction pattern width.
The relations developed above will be useful for determining the effect of
changes in slit width on the signal to noise ratios and the resulting changes
in scan speed and time constant.
The products of the terms (J/J ) and (dv/ds) which depend on (s/a) are
shown, raised to the appropriate powers, on Figure 5.U.3.1*. *br slit widths
greater than about 2a the effects of diffraction on scan rate ratio or time
constant ratio are not important.
5.U.U Time Constant-Scan Speed Relations
The selection of the lock-in amplifier time constant and the monochromator
scan speed will depend on the spectral and temporal nature of the object of
interest. In those cases in which the source of interest varies appreciably
with time, this fact will dominate the choice of scanning speed. Particularly
5-21
-------
0.01
0.001
0.0001
Figure 5.h.3.h Diffraction Parameters
5-22
-------
in these cases it will be helpful to scan no wider a region than
The lock-in amplifier time constant would be chosen to be compatible with the
selected scan speed based either on the criterion of the permissible wave-
number shift or of the permissible error at the peak of the slit function
representing a spectral line as described in this section.
itor cases in which the source of interest is not varying appreciably
with time, a choice of scanning speed is possible.
The lock-in amplifier'time constant selection from 0.01 sec. to 1.0 second
allows control of system bandwidth and noise. Generally, the shortest time
constant consistent with a satisfactory noi8e level should be used. Longer
time constants will reduce noise but also degrade the system ability to
respond to a rapidly changing signal, i.e., a spectral line.
Consider a triangular pulse (representing the spectral response to a narrow
line) as the input to a low pass RC filter. The filter output has two major
distortions; there is a delay and there is an error at the peak (see Figure
5.U.U.1).
If the time constant, T = RC, is short compared to the pulse width at
half height, At = AX/(dA/dt) = W(dN,/dt), then the delay will approach T for
both the rising and falling portions of the output pulse. The peak will be
delayed a^out 0.69r and the peak error (for a unit input peak) will be about
0.697/At.
For the rising portion of"the input, e± = at = (l/*t)t and the output is
-t/RC
e = <*(t - RC) + orRC e
o
For the falling portion of the input, e = 1 - art' with a shift of the
time axis to the input peak. Assumingthe rising portion of the output is
negligibly different from its asymptotic rate of change, the output is
-t '/EC
e = 1 - a(t'-RC) - 2&-RC
o c
Differentiating e and setting it to zero leads to a time delay of the peak,
t' = 0.693RC = 0.8931-. The error in the output peak is
n
5-23
-------
* 0.69T -H I-*-
:*: C e
\V °
T -*\\»-
Assvune negligible source impedance and load.
* T «At
Figure 5.U.U.I RC Filter Response
5-2U
-------
E •(«, - e )/eJ = 1 - e = 0.693<*RC = 0.693f/At
p ip op" ip op '
If the delay is set equal to the time corresponding to the smallest
resolution element T = 0.1 cnfV(clM/dt) and from the wavenumber calibration,
dv/dt = (RPM/60)B, where RPM = Monochromator scan speed and B is the number
of cm per drum turn,
0.1(60)
Td = (RFM)B
For the 2UOL/mm grating, B = 123.9 cm^/turn and, at the fastest speed of
6 RPM, T = 0.008 sec. For the lOlL/mm grating, B = 52.2 cm^/turn and, again
at 6 RPM? T = 0.02 sec. Thus, within a factor of two, a time constant of
about 0.01 sec is appropriate for the fastest scan speed. Figure 5.^.2 shows
the time constant corresponding to 0.1 cm"1 delay for the available scan speeds.
For other time constant settings the delay in cm'1 is proportional to the T
setting. Values may be obtained by the ratio
Delay (cm"1) = — (0.1 cm'1)
Td
where T may be read from the figure.
d
Note that, for either grating and a 0.1 cm" delay,
T (RPM)(L/mm)-' 0.l(6o)(L/mm)/B
d
H.6 *- 12.
This is a useful relation if operating charts are not at hand.
Let the value of At be evaluated for the best specified resolution of
0.01 micron. The corresponding values of Av vary from 11.1 cm" at 3333 cm
(3n) to 3.3 cm"1 at 1820 cm"1 (5.51J-) for the 2hO L/ram grating and 2.0 cnT
at 1*130 cm'1 (7n) to 0.55 cm'1 at 7^0 cm'1 (13.5n) for the 101 L/mra grating.
5-25
-------
T = Time Constant Setting
T = Time Delay
d
T, for
a
0.1 cm
Delay
-1 0.03 -
Delay cmT
Tdchart
0.01
0.003 •
0.001
N - RPM
-1
Figure 5.'kU.2 Time Constant - 0.1 cm Delay
5-26
-------
Av60
At =
(RPM)B
6 RPM
At
O.$)0
0.27
0.38
0.10
T
0.008
0.008
0.02
0.02
0.69T/At
0.006
0.020
0.036
0.138
2^0 L/mra 3p, 11.1 cm"1
5.5H 3-3
101 L/mm 7P- 2.0
13.5n 0.55
Thus, the peak error grows with wavelength and, for this fastest scan
speed, reaches about lU$ at 13-5 microns even with the short time constant.
This can be reduced by decreasing the scan speed. Figure 5.k.k.3 shows the
peak error for the spectral band of each grating for the range of available
scan speeds and a time constant setting' of 0.01 second and a spectral bandwidth
of 0.01 micron.
From the figure it may be seen that in order to have 1% or less peak error
over the 3 to 5.5 micron band a maximum speed of about 3 RPM can be used.
Similarly, for the 7 to 13.5 micron band a speed of no more than about 3/k RPM
can be used for a 1$ peak error. The peak error for other time constants and
spectral bandwidths is proportional to (r/AX). Thus for T = 1.0 sec. and the
101 L/mm grating (AX = O.Oln) a scan speed of 3/32 RPM win give about .001
(1.0/0.01) ~ 0-1 or 10$ peak error at 13-5 microns and about 3% peak error at
7 microns. With the 2^0 L/ram grating (AX = O.Olji), N = 3/32 RPM and T = 1.0
sec. the peak error is about h% at 5.5 microns and about 1% at 3 microns.
From Figure 5.U.U.2 the delay with T = 1.0 sec and NI= 3/32 RPM would be about
0.08 cm"1 with the lOlL/mm grating and about 0.2 cm~ with the 2UO L/mm grating.
It is evident that for the maximum resolution the scan speeds must be slow
in order to avoid distortion particularly of the output peak amplitude. How-
ever, note that even with error at the peak, a better approximation to the peak
can be obtained by extrapolating the two sides of the slit function to an
intersection if T < At.
A logical approach to the selection of the proper time constant and scan
speed is shown on Figure 5.U.U.U. The diffraction parameters are omitted for
brevity but should be included in the calculation if the slit width is
comparable to a.
5-27
-------
1.0
0.1
Peak
Error
0.01
0.001
0.0001
Unit Peak Input.
T = 0.01 sec
Peak Error oc -r-
AX
32 16 8 U 2
5.I4.'i.3 Time Constant - Peak Error
5-28
-------
\
No Solution
for
This S/N Limit
No Solution
for
This S/N Limit
and Run Time
C*lc.(S/H) 1 • • Mguc(s/lf) Input
Ji^^ Run Time Limit
HB4^yjIx^^.Yiei8i _. , . Band: v - \»
^^^^s^ Reaol.-* Max s
f ^S^^^ f 1^
Calc. Run Time v _v '^'^
V"7^~~Atl °r dv/dt
* ^bv«
<^>>
| Run | T
1 *i.
1 ml
No ^T.
21 T = At T
-------
Since the value of Av varies considerably over a wide band (vu - vp it
la convenient to use a mean Av for the band defined at a geometrical mean
navenumber, v , since AX does not change markedly over a band.
2
Av e AX v
m o
J5B Ji
vi* vm
Assuming AX is constant ,an average Av may be calculated.
Av
/ \ fVu A ,»
(v ~ v *)=/ Av dv
xvu * J
v /v, + 1 + v,/v
j U *
Av = Av
m
Av/Av is less than 1.3 for values of v /v/ of Z.k or less of the present
v/ m u
instrument.
Tor the laboratory case v falls in the CO band and is moved to 2500 cm" ,
The values of s and Av correspond to AX ~ 0.01 micron.
m
The number of mean slit functions in a scan is (v - v,)/^m> The time
to scan a band is T -((vu - O/AvJ/K^ = (vu - v^VCSv/dt^ where &n is the
time to scan * mean slit function.
*»
Band v s Av
m m
3-5.5^ v /v^j = 3600/1500 = 2.h (2500) cm"1 700n 6.2 cm"1
7 - 13.51* «= lUlO/760 = 1.86 1000 cm"1 300>i 1.0 cm"1
Assume there are n resolution elements, At , in a mean slit function.
m r
5-30
-------
Av At
m m
m c Av At
r r
where At = time to scan a mean silt function, Av and
m in
At = time to scan a resolution element, Av .
r r
Note that Av and At are related, in general, by the constant scan rate.
Av = At (dv/dt)
At the upper and lower limits of the band
Av /v X2 Av /v,\2
u / u \ , * I I \
-— = ( — I and -— = I — I
Av V v I Av \ v /
m \ m / m V m'
The number of resolution elements in the spectral slit width at the upper
and lower limits of the band are
2
Av Av (v /v ) ^
n u = mum = n (v /v ) = n (v7v ) and
u Av Av mum m u *
r r 2
Av Av (v /v ) 2
n = —- = —-—-—— = n (vYv ) = n (v /v )
i Av AV m * m m L u
r r
since v /v = v /v = (v /vj . If n =10 and v /v = 3, n = 3.3 and n = 30.
u m nr Jfc u A m u £ A u
Let the time delay At eqioal the time constant, T.
d
At = T = K At
d r
= K At /n = K —77-
m' m dv/dt
Prom the peak error relation,
E - 0.7 T/At = 0.7 T/n At = 0.7 T/n (r/K)
p m m r m
«= 0.7 K/n
in
5-31
-------
If At /T * 3,(K/n ) ~ 0.3 and E ~ 0,23.
mm P
max
If, for example, K = 1 and n = 10, K/n « 0.1 Ep = 0.07
7 m m
K = 1/3 and n = 10, K/n « 0.03 EP - °-02
m 'm
Finally,
At = n At
m m r
n
m
1, . K m
T n n n dv/dt
m m
The time per resolution element is given on Figure 5.^.5 as calculated
from Av/(dv/dt) = Av/((RPM/6o)B).
Time Per Resolution Element (Sec)
Scan Speed (RPM)
Grating Resol. 3/32 3/l6 3/8. 3/U 3/2
2UOL/mm
101L/
mm
0.1 cm
0.2
0.5
v • s
1.0 *
2.0
0.1
0.2
0.5
1.0 *
2.0
0.52
1.0
2.6
5.2
10. U
1.3
2.6
6.U
13.
26.
0.26
0.52
1.3
2.6
5.2
0.6U
1.3
3.2
6.U
13.
0.13
0.26
* 0.6U
1.3 -
2.6
0.32
0.6U
1.6
3-2
6.U
0.06U
0.13
0.32
0.6U
1.3
0.16
0.32
0.8
1.6
3.2
0.032
o.o6U
0.16
0.32
0.6k
0.08
0.16
o.U
0.8
1.6
0.016
0.032
0.08
0.16
0.32
o.oU
0.08
0.2
O.U
0.8
0.008
^
0.016
o.oU
0.08
0.16
0.02
o.oU
0.1
0.2
o.u
Values in this line also equal dt/dv - Sec/cm .
Figure 5.U.U.5 Time per Resolution Element
5-32
-------
6.2 cm
10
/- -1
0.6 cm
1.0 cm
10
0.1 cm
In order to illustrate use of the above relations, consider the two spectral
bands of interest run at the maximum specified resolution, AX = O.Oln, and with
the maximum time constant, T = 1.0 sec. Assume the criterion At /T = ID for
m
E ~ 0.07.
P
Band (approx.) 3-5.5 Micron 7 - 13.5 Micron
-1 -1
v -v (assumed) . 3600-1500 cm lUlO-760 cm
VI L
Grating 2^0 L/mm 101 L/mm
Av
m
At /T
Av T/At
m m -1-1
Av /At (~dv/dt @ T = 1.0) 0.6 cm /sec. 0.1 cm /sec.
m m . -1-1
At /&v 1.6 sec./cm 10 sec./cm
m m
N (closest * value, Fig. 5.U.I*.5) 3/8 RPM 3/32 RPM
T Runtime ~ 1 Hr. ~1.8Hr.
T (at N, from Fig. 5.U.U.2) ~0.3 sec. ~1.2 sec.
Delay (= T) 1.0 sec. 1.0 sec.
(=(T/T )0.1) ~0.3 cm 0.1 cm
K/n (=E/0.7~0.1) 0.1 0.1
m p
n (K assumed = 1.0) 10 10
m
n (= n v /v ) at v 2h 19
u m u' I u
n (= n v /v ) at v h 5
I m A' u £
At (=At /n ) 1.0 sec. 1.0 sec.
r mm
Av (= At /(dv/dt)) 0.6 cm" 0.1 cm
r r -1-1
Resol. Setting (closest value) 0.5 cm 0.1 cm
No. of data points ~ 1*200 ~ 6500
Note that there are 2n data points in the total slit function width, 2Av. If
K had been assumed equal to 2 there would still be U to 5 resolution elements in
the total slit function width at v . In this case,the resolution setting would
be about 1.0 and 0.2 cm for the two bands and the number of data points would
be reduced by a factor of 2 from those listed above.
The long run times shown above make it clear that the band limits should be
reduced as much as possible especially when high resolution is required. For
other types of runs the appropriate assumptions may be different from those given
above but the general procedure should be the same.
5-32A
-------
5.U.5 Selective Amplifier Q
Jt>r most test conditions a Q of 10 will be found to be satisfactory.
Because the selective amplifier takes an increasing time to respond as Q
is increased there are operational limits on the Q setting, especially at
the faster scanning speeds.
The envelope response of the selective amplifier can be expressed in
terms of a decay time constant, T = Q/nf, where Q is the Q control setting
and f is the tuned frequency. Using the lower tuned frequency of 330 Hz,
T =
Q rr(330) 1000
or Q = 1000 T
Q
If T is set equal to the lock-in amplifier time constant (see
Section J.b.k), which has a range of 0.01 to 1.0 seconds, the range of Q
settings will be from 10 to the maximum Q of 100.
For the fastest scan speeds (for which T = 0.01 sec. is appropriate) a
Q of 10 is satisfactory. A higher Q, will cause a more sluggish response.
At the lower scan speeds a Q higher than 10 may be used. However, the amplitude
and phase response are much more critical with high Q than at low Q.
Figure 5.U.5.1 shows the relative amplitude response of the selective
amplifier as a function of Q and (f/f ) where f is the signal frequency and
f is the tuned frequency. Since it is difficult to obtain values near f
from a figure such as this, another plot is shown in Figure 5,^.5.2 which is
particularly useful at frequencies near f . Figure 5»^»5«2 shows the departure
of the response from unity on a log scale as a function of Q and Af/f where
The phase response of the selective amplifier is shown in Figure 5. ^.5-3
as a function of Q and f/f . Note the very large changes in phase near f
for high values of Q. Changes in the phase can result from drift in either
selective amplifier tuned frequency or from drift in the chopper frequency.
One reason for using a Q of 10 in the selective amplifier is that there
is a tuned amplifier in the lock-in amplifier reference section with a fixed
Q of 10. With a fixed input and equal values of Q a similar drift of the
selective amplifier and lock- in reference tuned amplifier frequency will
produce no relative phase shift (although an amplitude change occurs in the
5-33
-------
3 4567891
4 567891
Y1
i.Ol
0.1
1.0
= f/f
10
100
Figure 5.U.5.1 Selective Amplifier Relative Response
-------
Y1
u>
vn
0.001
0.0001
Figure 5.^.5.2 Selective Amplifier Relative Response Near f
-------
.60
-90
0.01
100
*/*
Figure 5.^.5.3 Selective Anqplifier Phase Response
-------
selective amplifier, of course). With the selective amplifier Q * 10 there
will be a relative phase shift as well as the amplitude change. If the
selective amplifier and the lock-in amplifier reference section tuned amplifier
are fixed and both have a Q of 10 then a shift in the input frequency will
cause an amplitude change in the selective amplifier but no relative phase
shift. If the Q's are not the same this input frequency shift will produce
a phase shift as well. Therefore, if possible, a Q of 10 is recommended for
the selective amplifier under ordinary conditions.
5.5 PROCEDURE
In this section procedures are given for setting the various controls
according to the type of test being run, the chosen test parameters and the
type of recording desired. Tests may be made in either the emission or
transmission mode of operation. Either analog or digital records may be made
independently or both may be made simultaneously.
First, turn on the power to all components to be used. Since some components
do not have a separate power switch the following table shows a summary of the
sources of power for these components. (Note that the tape recorder power
switch is inside the plastic cover below the left tape reel.) The other power
switches are clearly labelled.
Sources of Powej:
(for components not having a separate power switch)
Source
Detector (bias) ™ BIN
Source Synch Preamplifier NIM BIN
Reference Synch LED and Diode Logic Chassis
Encoder Logic Chassis
Preamplifier NIM BIN
Selective Amplifiers N3M BIN
Lock-in Amplifiers NIM BIN
Source Synch Amplifier Logic Chassis
Ref. Synch Amplifier Logic Chassis
Standard Signal Logic Chassis
Source Compensation Amplifier Logic Chassis
Ref. Compensation Amplifier Logic Chassis
Wavenumber Generation System Logic Chassis
5.5.1 Monochromator
The procedure for setting the various monochromator controls is given in
this section.
5-37
-------
The grating is selected ac.ording to the wavenumber band being used and
the grating in use can be obs-.-rved through transparent plate under a cover
on top of the nonochromator. Tiie lid of the monochromator does not. have to
be removed to change the grating. The round cover be easily removed by simply
pulling upward. The grating nearest the paraboloid is the grating in use and
L/MM labels have been attached to the grating mount to identify the grating
location.
If the desired grating is not in position it can be placed there by rotation
of the grating mount. Rotation is accomplished by means of the knob in the
center of the transparent plate. The knob controls two prongs which, when
the knob is pushed down, engage a pin on the grating mount. While holding
the knob down (thereby keeping the pin engaged) gently turn the knob in the
direction it will go easily until an abrupt resistance to rotation is fe.lt.
Magnets on the grating mount hold it against stops on the grating mount support
at the ends of the rotation range. Release the knob and replace the round
cover.
The filter associated with each spectral hand may be brought into place
in front of the entrance slit by means of a knob on top of the monochromator.
The knob actuates a filter wheel in which the filters nave been mounted.
Besides the two positions for the two spectral bands there are OPEN and SHUT
positions of the control knob for which a large hole and a blackaned plate
respectively are placed in front of the entrance slit.
The width of the entrance and exit slits are equal and may be set by
means of a micrometer drxrni which reads directly in microns. One turn equals
100 microns and the number of turns is marked on the housing. A range of 20
turns gives a maximum slit opening of 2000 microns or 2.0 mm.
The height of the opening at the entrance slit may be set by means of the
micrometer control on top of the monochromator. The micrometer reads the slit
height directly in millimeters. One -turn equals 0.5 mm and the range is from
0 to 12 mm. For the most precise adjustment the micrometer should be net by
decreasing the reading.
Wavenumber is set by means of a wavenumber drum on the monochromator.
The drum is graduated on an arbitrary linear scale; after set up according,
to Section 5.5.2 the wavcnuaiber may be read directly on the bidirectional
counter in one of the electronic consoles.
The wavenumber drum is divided into 100 divisions per turn and a turns
counter (0 to 2k times) is provided. Mechanical stops limit the rotation
from a drum reading of about -0.62 (reading = 23.38) to about + 23.73 drum
5-38
-------
turns. The drum should not be turned hard against these stops or the wave-
number calibration may be affected. Electrical switches in the wavenumber
scanning mechanism are set to stop the drive before the mechanical stops
are reached.
If the monochroraator control panel power is on, the wavenumber drum cannot
be turned by hand unless the SPEED CONTROL on the control panel is set to N
(for Neutral).
The wavenumber drive turns the wavenumber drum at speeds set by the
SPEED CONTROL knob on the monochromator control panel and by ratio gears on
the back of the wavenumber drive. Wavenumber drum speeds from 6 RPM to (3/32)
RPM in steps of 2:1 ratio are provided. See Section h.2.7 for more details
of the wavenumber drive. Select the proper gear ratio and SPEED CONTROL setting
for the speed desired. Normal scanning is in the direction of increasing
wavenumber (or drum reading) with the scan direction control switch in the UP
position. To start scanning turn on the X DRIVE switch. If desired, the
analog recorder chart can be simultaneously controlled by the X DRIVE switch by
turning on the CHART switch on the monochromator control panel and placing
the REMOTE/LOCAL switch on the analog recorder in the REMDTE position.
5.5.2 Wavenumber Generation System
The procedure for setting up the wavenumber generation system is described
in this section. (Be sure that the COUNTER X OUTPUT and COUNTEPv Y OUTPUT
terminals on the logic box are connected to the COUNTER INPUT X and COUNTER
INPUT Y terminals, respectively, on the electronic console panel beneath the
DVM's.
1. .Select the 3 to 5.5 micron or 7 to 13.5 micron setting of the BAND
SELECTOR on the NDDE SELECTOR section of the control panel according to
the range being used.
The equations for the wavenumber are posted above the bidirectional counter
and are of the form:
Wavenumber - A + B (WD)
2. Set the wavenuraber drum to zero
3. Set the MODE switch on the bidirectional counter to CONT.
k. Set the DISPLAY TIME control on the bidirectional counter to KIN.
5. Set the ZERO/SET switch on the bidirectional counter to SET.
5-39
-------
6. Set 10(A) on the SET s-Axtcbas oi t.he biiLrectional counter (counter readc
in 0.1 wavenumbcr unltr-).
7. Set 10(B) on the COARSE and FINE selectors on the ENCODER CONTROL section
of the control panel (again in units of 0.1 wavenumbers) by adding the coarr,c
and fine readings. For B = 52.6, for example, set 500 on the COARSE
SELECTOR, 20 on the TENS dial and 6 on the ONES dial of the FINE SELECTOR.
8. Push the RESET button on the bidirectional counter. The number 10(A)
should appear in the bidirectional counter window. If the number in the
bidirectional counter- window does not change on. pushing counter RESET,
most likely the coupler is generating a hold command. Push the RESET
button on the coupler to clear temporarily. To remove the hold place
the coupler FUNCTION switch to RECORD ONLY.
9. Run the wavenumber drum up to 1.00 turn and observe that 10(A+B) is dis-
played in the bidirectional window. Run the wavenumber drum back to zero
and observe that 10(A) is again displayed in the bidirectional counter
window. Deviations of one or two units are sometimes observed and are
normal. (Alternatively, one may place the ZERO/SET switch of the bi-
directional counter on ZERO and (with VJD = 0) push RESET; the bidirectional
counter vail then read 10(B) at WD = 1.00 and should return to zero at
WD = 0. Reset ZERO/SET switch to SET and set 10(A) as in step 6.)
10. If these readings are observed the wavenumber system is ready for operation.
5.5.3 Amplifiers-Emission
This section contains the procedure for setting up the amplifiers for
operation in the emission mode. Be sure the NDNITOR output terminal of the
reference lock-in amplifier (at the far right) is connected to the SOURCE
LOCK-IN INPUT terminal on the control panel (actually the input to the source
compensation amplifier).
It is assumed that the system has been set up and started as described
in Section 5.2 and 5.3, that the test parameters have, at least, been
tentatively selected ac indicated in Section 5,'-:- and that the wavenumber
generation system has been set up as give.: in Section 5»5«2.
1. Set the OPERATE/STD SIG. switch on the control panel to STD SIG
2. Lock-in amplifier
a. Set the METER/143N swatch to the REF position.
b. Set the TIME CONSTANT to 0.1 sec.
c. Tune the FREQUENC'i control to maximize the meter (about 330 Ilz) reading.
A reading of about 0.80 of full scale should be observed on the lock
in amplifier meter with a norm-,! setti.-ig of the REFERENCE LEVEL control.
-------
3. Selective Amplifier
a. Set the gain to X10
b. Temporarily set the Q control to 100 to make tuning more precice.
c. Set STD. SIG T ADJUST to full scale (=1000)
d. Set the FREQUENCY control on the selective amplifier to give a
maximum reading on the lock-in amplifier meter
e. Set the Q control to the test value
f. Set the GAIN control to XI.
h. Set the wavenumber to a large signal region and open the slits test value.
Previous SYSTEM OPERATING LOG settings will be helpful. The slits may be
temporarily widened until a signal is observed and initial settings made.
5. Preamplifier
a. Set the lock-in amplifier GAIN to 10
b. Set the OPERATE/STD SIG switch to OPERATE
c. Set the preamplifier GAIN as high as possible without overloading
the selective amplifier or lock-in amplifier
6. Lock-in Amplifier
a. Set the METER^DN switch to PSDX1 (phase sensitive detecting XI meter)
b. Adjust the PHASE switch and dial to give a maximum meter reading.
If the meter goes off scale decrease the preamplifier GAIN and
repeat the phase adjustment.
7. Decrease the monochromator slits to the test value
a. Readjust the preamplifier GAIN to obtain a half scale to full scale
lock-in meter reading. If necessary, increase the selective amplifier
GAIN to 10X and, if further required, increase the lock-in amplifier
GAIN.
8. Lock-in Amplifier
a. Scan the monochromator slowly by hand over the spectral region of
interest and find the maximum positive meter reading. Note the
reading.
b. Repeat step a except for the maximum negative reading. If the meter
goes below zero, switch on the ZERO SUPP switch and adjust the ZERO
SUPP dial to keep the signal above zero.
-------
c. Recheck a. and reduce the preamplifier gain if necessary to keep the
maximum positive signal on scale.
d. The entire signal range should now be within the limits of zero and
full scale of the lock-in meter.
e. Set the lock-in amplifier TIME CONSTANT to the value desired in the
test.
9. Data Acquisition System
a. Set T to 125 (1000 full scale)
sig
b. Turn the 5^03-010 DVM FUNCTION switch to VOLTS and the RANGE
switch to 10
c. Plug INPUT of the 5^03-010 DVM into the SOURCE COMP OUT terminal of
the control panel.
Observe the voltage on the DVM at the wavelengths for the maximum
negative and maximum positive signals to see that the signals remain
positive on the DVM and are less than 10 volts.
d. Set the RESOLUTION SELECTOR to the desired resolution for the digital
system.
10. Optical Zero
a. Place the filter wheel at the monochromator entrance" slit in the
SHUT position
b. Observe the DVM and lock-in meter reading for optical zero.
11. A check scan can be made on the analog recorder if desired.
a. To record the spectrum- set the analog recorder input selector to I.
The recorder is connected to the source compensation amplifier output.
Set the recorder to an appropriate scale and speed and scan the
spectrum (see Section 5«5«6)«
12. System Operating Log
a. Make a complete record in the SYSTEM OPERATING LOG for each run.
5.5.14. Amplifiers-Transmission
This section contains the procedure for setting up the amplifier for
operation in the transmission mode. Be sure the MONITOR output terminal of
the reference lock-in amplifier is connected to the REF LOCK-IN INPUT terminal
on the control panel and the MONITOR output terminal of the source lock-in
amplifier is connected to the SOURCE LOCK-IN INPUT terminal on the control
panel, (as noted before, these terminals designated LOCK-IN INPUT are, in
fact, inputs to the compensation amplifiers).
-------
It is assumed that the system hac been set up and started as described in
Section 5.2 and 5«3> that the test parameters are known (Section 5.U), and
that the wavenumber generation system has been set up as deocribed in Section
5-5.2.
1. Set the OPERATE/STD SIG switch on the control panel to STD SIG
2. Lock-in Amplifiers
a. Set the METER MON switch of both lock-in amplifiers to REF
b. Set the TIME CONSTANT of both lock-in amplifiers to 0.1 sec
c. Tune the FREQUENCY control of the source lock in to maximize its
meter reading (about 570 Hz).
d. Tune the FREQUENCY control of the reference lock-in amplifier to
maximize its meter reading (about 330 Hz). (These readings c. and d.
are normally about 0.8 of full scale with the normal setting of the
REFERENCE LEVEL control.)
e. Set both lock-in GAIN controls to 10.
f. Set the METER/MON switch of both lock-in amplifiers to SIG
3. Selective Amplifier
a. Set the gain to X10
b. Temporarily set the Q control oi' both selection amplifiers to 100 to
make tuning more precise.
c. Set STD SIG T ADJUST to full scale(=1000). Note: If only the reference
chopper is being used, set STD SIG T ADJUST to zero to reduce noise from
unused source channel.
d. Set the FREQUENCY control on both selective amplifiers to maximize the
corresponding lock-in amplifier meter reading.
e. Set the Q control of both selective amplifiers to the test value.
f. Set the GAIN control of both selective amplifiers to XI.
k. Set the wavenumber to that for the peak signal for the wavenunber interval
being used and open the slits to the test value. (Previous SYSTEM OPERATING IfJ.
settings will be helpful.) The slitc may be temporarily widened until a
signal is observed and initial settings are made.
5. Preamplifier
. a. Set each lock-in amplifier GAIN to 10.
b. Set the OPERATE/STD SIG switch to OPERATE.
c. Set the preamplifier GAIN as high as possible without overloading the
selective amplifiers or lock-in amplifier.
-------
6. Lock-In Amplifiers (Reference Balance Procedure)
a. Set the METER/MDN switch of both lock-in amplifiers to PSD x 1 (pha.-.o
sensitive detector; X/meter) Be sure the ZERO SUPP switch of both lock
in amplifiers is at OFF.
b. Block the reference beam at the intermediate focus with a blackened
plate.
c. Adjust the PHASE switch and dial of each lock-in amplifier to maximize
the lock-in meter reading.
d. Readjust the preamplifier gain, if necessary, to give a meter reading of
about half scale to full scale.
e. Connect the INPUT of the 5^03-010 DVM to the REF COMP AMP OUTPUT
terminal on the control panel. Set the DVM FUNCTION switch to VOLTS
and the RANGE switch to 10.
f. Adjust the reference lock-in GAIN ADJ control until the DVM reading is
a minimum (a few millivolts).
g. Remote the reference beam block and observe tho DVM reading. The ref
lock-in meter will go off scale negative; this is normal.
h. Block the source beam between the telescope and the reference chopper
and observe the DVM reading.
i. The readings from g. and h. should be equal within about 1% of the
reading or less. If not go to step b. and go through the reference
balance procedure again.
j. If the gains of the selective amplifiers or lock-in amplifiers are
changed the reference balance procedure should be repeated. The
GAIN and Q, settings of the reference selective amplifier should always
equal the GAIN and Q settings of the source selective amplifier.
The GAIN and TIME CONSTANT settings of the reference lock-in amplifier
should always equal those of the source lock-in amplifier.
7. Scan through the spectral region to be sure the source and reference signals
do not go off scale.
8. Select .and set the wavenumber region to be assigned a known or arbitrary
relative transmission.
9. Be sure the INPUT of both DVM's are connected to the SOURCE COMP AMP OUTPUT.
10. Connect the DVM RATIO INPUT below the 5^03-010 DVM to the REF COM? AM?
OUTPUT.
11. Set the FUNCTION switch of the 5^03-010 DVM to 10X RATIO.
12. Set the known or arbitrary relative transmission on the 5^03-010 DVM by
means of the T . control.
sig
-------
13. Check scans can be made on the analog recorder if desired.
a. To record I, set the analog recorder input selector to I. The
recorder is connected to the source compensation amplifier output.
Set the records to an appropriate scale and speed and scan the
spectrum (see Section 5»5«6).
b. To record I , set the analog recorder input selector to I . The
recorder is connected to the reference compensation amplifier output.
Set the recorder to an appropriate scale and speed and scan the
spectrum (see Section 5.5.6).
c. To record I/I set the analog recorder selector switch to I/I • T06
recorder is connected to the output of the I/I ratio module. Set
the recorder to an appropriate scale (I/I =1.0 gives 1.00 volt to
the recorder)and speed and scan the spectrum (see Section 5.5.6).
1^. System Operating Log
a. Make a complete record in the SYSTEM OPERATING LOG for each run.
5.5.5 Data Recording Systems
The procedures for setting up and using the recording systems are described
in this section. The two systems (analog and digital) are described separately
since they may be operated independently.
Analog Recording System
The procedure for operating the analog recorder itself is virtually identical
to that described in the Hewlett Packard 7701A and preamplifier 8801A manuals.
The basic procedure is given here. Refer to these manuals for more details.
Those features of operation unique to the ROSE system are discussed below.
The inputs to the recorder pass through an input selector switch located
just to the left of the recorder. This switch has three positions by means
of which the recorder input is connected to the following:
Position Voltage Source
I ~10V max Source Comp. Aropl. Output
I ~10V rax Ref Comp. Ampl. Output
I?I ~1V max I/I Ratio Module
' o o
It should be noted that the I/I ratio module has a negative voltage output.
In order for the recorder to read up scale in the normal manner the leads to
the recorder have been reversed and both leads must float with respect to ground.
5-1*5
-------
The REMOTE/LOCAL switch is connected co that, in the REMOTE position, the
recorder will run (il the ClI/VKT switch on the monochromator control ir. ON)
whenever the X DRIVE switch is turned on.
It is emphasized that great care should be used in replacing the chart
paper not to bend the galvonometer or event marker arras.
The following procedure should be used to set up for analog recording.
1. Set up the wavenumber generation system as discussed in Section 5. 5. 2.
2. Attach the pushbutton switch on a cord to the MANUAL INPUT jack on the
recorder panel to the left of the analog recorder.
3. Set the input selector switch to the desired position: I, IQ or
1*. Set the REMOTE/LOCAL switch to REMOTE (and CHART switch on mono chroma tor
control to ON) for simultaneous records chart and scan drive operation.
(Set the REMOTE/LOCAL switch to LOCAL for independent analog recorder
operation).
5. Select the recorder chart speed by selecting MM/SEC or MM/MIN and
pushing one of the numbered pushbuttons.
6. Select the V/DIV range (I & I are 10 V max; I/IQ ~ 1.0V max). The
chart is 50 divisions wide.
7. Push the red button in the center of the V/01V switch to connect the
analog recorder to the source.
Digital Recording System
The following procedure is to be used to set up the digital recording system
1. Bidirectional Counter
a. Set the FUNCTION switch to (X-Y) and the NORMAL/REVERSE switch to
NORMAL.
b. Set the LIMIT thumbwheel switches to +99999-
c. Set the MODE switch to CONT. and the DISPLAY TIME switch to MEN.
d. At the rear: set FAST/ NORMAL switch to FAST. X1/X2/XU may be
in any position.
2. 5^03-015 DVM (upper)
a. Set the READ/HOLD switch to HOLD.
3. 5^03-010 DVM (lower)
a. Set the READ/HOLD switch to HOLD.
b. Set the FUNCTION switch to 10X RATIO.
-------
U. Digital Printer
u. Be sure there is sufficient paper in the printer (system will halt
if paper runs out).
b. Press OPER button (operate).
c. At the rear: A1J1 switch should be down; A1J2 switch up.
5. Digital Coupler
a. Set the OPERATE/STANDBY switch to STANDBY.
6. Tape Recorder
a. Load tape into the tape recorder.
(a tape threading diagram is located on the inside of the recorder cover.
b. Press LOAD FORWARD. Tape should feed into the recorder until a silvery
patch stops near the large head and the READY light on the tape
recorder should come on. The TAPE NOT READY light on the coupler
should extinguish.
7. Press the RESET button on the coupler to extinguish the coupler WRITE
ERROR light.
8. Press the tape recorder FILE GAP button.
The digital system is now ready for the first run; see Section 5.5.6
for procedure in scanning a spectrum.
5.5.6 Scanning the Spectrum
The prcedure to be used depends on the method of recording to be employed.
It is not necessary to set up the digital recording system if only the analog
records are to be made. The procedures for each type of recording is given in
the following sections. If both analog and digital recordings are to be made,
set up both the analog and digital system as indicated in Section 5«5-5. All
of the procedures in the Analog Recording Procedure below except step 6 are also
in the Digital Recording Procedure. That step should be added to the digital
procedure if both types of recordings are to be made.
Analog Recording
It is assumed that the Wavenumber Generation System has been set up (see Sectior
5.5.2) and the Analog Recording System procedures have been followed (see Section
5.5.5).
1. Set the monochromator SPEED CONTROL to N.
2. Set the wavenumber drum of the raonochromator to the lower wavenumber
limit of the region of interest.
3. Set the SCAN UP/DN switch on the side of the wavenumber drive 1o UP.
-------
h. Set the monochromator SPEED CONTROL to SI, S2 or SU depending on the
scan speed desired. Consult the chart on top of the wavenumber drive
for the available speed (see alco Sections U.2.7 and 5.5.!.). Change
ratio gears if necessary to obtain the desired speed.
5. Turn the X DRIVE switch ON. This starts the scan and analog recorder.
6. For automatic marker operation place the MARKER SELECTOR switch to AUTO;
set the marker Av to 1, 10 or 100 cm as desired.
For manual marker operation place the MARKER SELECTOR switch to MANUAL;
watch the wavenumber display on the bidirectional counter and push the
event marker pushbutton at desired intervals.
7. Turn the X DRIVE switch OFF when the upper limit of the wavenumber region
is reached. (Be sure to do this; putting the SPEED CONTROL at N will also
stop the scan drive but the recorder will continue to run.)
8. Record the operating parameters in the SYSTEM OPERATING LOG and
the run number on the chart record.
9. Go to step 1 for the next run.
Digital Recording
It is assumed that the Wavenumber Generation System has been set up (see
Section 5.5.2) and the Digital RecordingSystem set up procedures have been
followed (see Section 5«5«5)«
1. Set the monochromator SPEED CONTROL to N.
2. Select PRINT ONLY, PRINT & RECORD or RECORD ONLY on the FUNCTION switch
of the data coupler.
3. Set the RESOLUTION SELECTOR ON THE ENCODER CONTROL section of the control
panel to the desired resolution (compatible with the scan speed). If the
RESOLUTION SELECTOR is set at OFF the digital system will not operate.
h. Load the counter SET thumbwheel switches with the run I.D. number.
5. Press RESET on the counter.
6. Press MAN SPACE on the digital printer h times (if the printer is being
used).
7. Record the run I.D. number by setting the coupler OPERATE/STANDBY switch
to OPERATE and pressing START on the data coupler k times. Set coupler
OPERATE/STANDBY switch to STANDBY.
8. If it is desired to check the operation on RECORD ONLY the digital printer
may be used by pushing MAN PRINT; the run I.D. appears at the right on
the paper.
5-1*8
-------
9. Press MAN SPACE on the digital printer (if the printer is being used).
10. Press FILE GAP on tape recorder (if the tape recorder is beinc used).
11. Reset the SET thumbwheel switches on the counter to the 10(A) value for
the spectral band being used.
12. Set the monochromator drum to zero.
13. Push RESET on the counter; if 10(A) does not appear in the counter window
push RESET on the coupler.
Ik. Set the wavenumber drum of the monochroniator to the lower wavenumber
limit of the region of interest.
15. Set the SCAN UP/DN switch on the side of the wavenumber drive to UP.
16. Set the monochromator SPEED CONTROL to SI, S2 or Sk depending on the
scan speed desired. Change ratio gears if necessary.
17. Set the coupler OPERATE/STANDBY switch to OPERATE.
18. Turn the \ DRIVE on. This starts the scan and the recording system. The
printer, if selected, will start printing. The tape recorder, if
selected, will move slightly with, each record.
19. Turn the \ DRIVE switch OFF when the upper limit of the wavenumber
region is reached.
20. Set the coupler OPERATE/STANDBY switch to STANDBY.
21. Press FILE GAP on the tape recorder (if the tape recorder is being
used).
22. Record the operating parameters in the SYSTEM OPERATING LOG.
23. Go to step 1 for the next run.
5.6 System Shut Down
Most of the equipment power can b'e turned off at any time but several com-
ponents should be turned off in a prescribed manner as described in this section.
5.6.1 Blackbodies
Use the followinc shut down procedure (based on the blackbody manufacturer's
recommendations) when the blackbody is not going to be used for a day or so.
1. Record the time, dial setting and controller meter reading in the BLACK-
BODY OPERATING LOG.
2. Turn off temperature controller power.
3. Wait one hour.
U. Turn off blackbody cooler power.
5-^49
-------
If the blackbody is to "be used again within 12 to 2k hours or so, uce
the following procedure.
1. Record the time, dial settingand controller meter reading in the
BLACKBODY OPERATING LOG.
2. Turn the dial on the temperature controller down to 500.
3. Leave the cooler running.
The manufacturer states that turning off the cooler when the temperature
controller is turned off should not cause a catastrophic failure (now that the
internal plastic hoses have been replaced by copper) but that such a procedure is
not recommended.
If the blackbody is left on stand-by at the 500 dial setting it would be
wise to have the temperature controller and cooler on the same 110V power
source. In that case, a power failure would cut off the temperature controller
as well as the cooler.
5.6.2 Detector Cooler
Use the following procedure for detector cooler shut down.
1. Record the cooler compressor SUCTION PRESSURE, OIL LEVEL and TIME
readings in the DETECTOR COOLER OPERATING LOG.
2, Record the hydrogen gage pressure, PSIA, and Dewar PRESSURE reading
from the thermocouple gage control in the DETECTOR COOLER OPERATING LOG.
3. Turn off the detector cooler compressor.
I*. When the Dewar PRESSURE reading exceeds about 20 microns or so turn on
the vacuum pump and, after a few minutes, open the Dewar valve. This
will ensure that any condensate on the cold finger from even small leakage
over protracted periods will not evaporate and build up pressure in
the Dewar.
If the detector cooler is not going to be used the next day
or so, wait until cold finger has warmed about 3 hours; close
the Dewar valve and shut off the vacuum pump. If the detector
cooler is to be used again in the next 12 to 2k hours it is
preferable to leave the vacuum pump on to ensure that the
Dewar is pumped out thoroughly.
5-50
-------
6.0 PERFORMANCE
The performance of the ROSE system described in this section is limited
to laboratory tests and initial field tests at a range of about.O.U km in
San Diego. The performance is described in terms of the expected vs
observed signal and noise. The performance in the field at longer ranges
(particularly with regard to the spectroscopic performance) will be
described in a forthcoming field test report.
6.1 LABORATORY TESTS
A number of laboratory tests of various parts of the system as well as
tests of the system as a whole have been made. Many of these were made
for functional checkout and will not be described here. Rather, emphasis
here is on the expected versus observed signal and noise of the system as
a whole. In addition, typical spectra obtained under laboratory conditions
will also be described.
6.1.1 Signal
The best place in the system to compare the expected versus observed signal
is at the source lock-in amplifier output. During the tests described here
(as well as in the field tests) the analog recorder (with the selector switch
in the I position) was connected to the source lock-in amplifier output. It
is now connected to the source compensation amplifier output to facilitate
emission mode measurements; future measurements equivalent to those described
here can be made by placing the analog recorder input selector switch in the
I position and setting the "T sig" control to 125 (1000 full scale). This
T sig setting combined with a gain of 8.0 in the source compensation amplifier
gives an overall gain of 1.00 between the source lock-in amplifier output and
the source compensation amplifier output.
First of all, it was established that the preamplifier gain could be taken
equal to the nominal gain and the selective amplifier and lock-in amplifier
were calibrated as described in this report.
With the source blackbody at its normal setting corresponding to l800K and
both choppers running, observations were made of the I signal for each grating
6-1
-------
and its corresponding filter for the following conditions (corresponding
to AX ~ 0.01 microns).
2500 cm
it
1000 cm
it
-1
-1
Slit
700 v. X 2.7 mm
700 n x 0.27 mm
300 u. X 2.7
300 H X 0.27 mm
lection
22
23-5
9
9
V/Div
O.OU.
ii
it
it
Sxs
0.88 volts
0.9k
0.36
0.36
These conditions were set up to give roughly the flux expected at simulated
ranges of O.U and U.O km with h/h =1.0. These spectral regions should be
reasonably free of absorption for the conditions reported here.
The calculation of the expected signal is based on the equation for S given
xs
in the Radiometry Section 3-3-1-
S = R T
xs de
AX
[
u
NO(X,T )-N°(X,T
s sww
/Art )M
tcl
In this equation, several factors may be neglected. N (X,T ) for a source
choppper temperature of 300K is negligible compared to No(X,Tg) for the
1800K source. The absorption a is taken equal to zero in the laboratory and
the factor (Aft /Afi ) is taken equal to 1.00 since h/h and s/h in the
t c o o
laboratory are very nearly zero.
The other factors are calculated as described in the Radiometry Section and
are listed below.
Slit
R
T p
1
5 -U 2 *
2500 700 p, x 2.7mm 0.5 x 10 V/W .11 3.5 x 10 cm ster O.OlOlp, 1.83
2500 700 ii x o.27
0.35 x
1000 300 p. X 2.7 1.2 X 10 V/W .13 1.5 X IQ-1
1000 300 u. X 0.27 " " 0.15 x 10"
0.0107U 0.097
I £
watts/cm steru
6-2
-------
These factors when combined with the modulation factor M = 0.63 and the
gain used in the observations give the following expected signals and
values of observed to expected signal ratio.
obs
v Slit G = G x G^ x G Expected S Ratio ——
p fs XS **> uXp
2500 700 n X 2.7. mm 200 = 10 X 1 X 20 1.60 0.55
11 700 p, X 0.27 2,000 = 100 X 1 X 20 1.60 0.58
1000 300 M. x 2.7 1,000 = 50 x i x 20 O.$k 0.67
11 300 n x o.27 10,000 = 500 x i x 20 0.5^ 0.67
The largest uncertainty in the expected signal estimate lies in the trans-
mission factor; e.g., the reflectivity of aluminized surfaces enters as
p in the transmission mode of operation. However, other factors undoubtedly
contribute to the uncertainty including aberrations and possible misalignment.
However, all alignments have been made with care. Aberrations for these slit
widths and heights would not be expected to contribute a large factor.
From these considerations, the observed signal is less than that expected by
a factor of 1.5 to 1.8.
6.1.2 Noise
U
Noise data taken at the same gain as the last run listed above, namely, 10 ,
and with a time constant of 0.01 sec showed peak to peak deflections of
3 divisions which corresponds to 0.12 volts pp at the source lock-in amplifier
output.' This results in an observed signal to peak to peak noise ratio of
about 3 for this fast scan simulation of long range conditions. By scanning
at the minimum speed and with a time constant of 1.0 second, a signal to noise c
ratio of about 30 would be expected based on peak to peak noise. Tests at G = 10'
and T = 0.01 second gave a noise voltage of 2 volts peak to peak on the recorder
(see Section U.I.6) which is equivalent to 0.20 volts pp for the gain used here.
Noise tests showed that the electronic signal amplification system will not
degrade the noise for reasonable gains. With a Q of 100 (t ~ 0.1 second)
and a lock-in amplifier time constant of 0.01 second the thermal noise of a
precision 10% resistor was observed at a gain of 10 but not at 10 . Operational
gains are substantially less than this, and the 10K thermal noise is only
about 1% of the detector noise.
6-3
-------
°f the 6Xpected noise ^r the above test c **
the above test conditions of 10 gain
the detector fioise, ,
microvolts ™s ive "6 U
.... !> Sives an expected output of (0.8 x 10 )(5)(K> ) -
0.04 volts if the noise were a constant synchronous signal. Of courte, the
long term average lock-in amplifier output resonse to noise is zero but
the short term average varies from zero. If the noise were to be alternately
in and out of phase with the reference signal a peak to peak output of 0.08
volts would be the result of a constant input of k microvolts rms. Since
the noise has a random amplitude the variation of the output should exceed
this value. If the above rms value is associated with the standard deviation,
o, of a normal distribution then deviations of about 3a (or 0.2U volts peak
to peak) should occur less than 1% of the time. Thus, the observed noise of 0.12 t
0.2 volts peak to peak is not inconsistent with that associated with the
detector noise alone. It is difficult, at this point, to define more precisely
the peak to peak noise indication on the analog recorder in terms of the rms
noise at the detector. Therefore, noise comparisons will be made in terms
of peak to peak recorder indication taking O.l6 V pp as that corresponding
to detector noise.
6.1.3 Typical Scans
A number of traces including those for which the data is given above are
jhown in Figure 6.1.3.1.
A portion of a wavelength CO calibration scan is shown in Figure 6.1.3.2.
The central line is the R5 line which is one of the stronger lines of the
band. The spectral width of the output of 0.9 cm" j.s about that expected
from the spectral slit width of O.?l cm" plus the full width at half
height of the absorptivity curve of about 0.28 cm" or a total of about
1.0 cm . The wavenumber indicated by the linear wavenumber drive was
within 0.2 cm of the value given by Plyler et al., in NBS Research 6k (1960).
Note that the resolution here is equivalent to about 0.002 microns, well
below the specified value of 0.01 microns.
Another scan shown on Figure 6.1.3.3 is that for ozone produced by a generator
and loaded into a cell which was placed between the source and receiver
telescopes.
6.2 FIELD TESTS
The field tests at a range of about O.U km in San Diego included tests made
with the identical conditions as those in the laboratory described above
6-U
-------
Figure- 6.1.3.1 Typical Laboratory
-------
v « 216
(Ply lei
""N. ^x*~" "S^
\-X
~-
\.
»5.6cm
• et al)
s
°-h
cm
2160 cm"1
1
^"* ^V X^"
\^s
i
-1
2170 cm
1
2165. 8,
observed
Figure 6.1.3.2 The R5 Line of CO
4-
1]
n
i
ail
--
1
J- •*• '1
/
L).
***i*f
\J
i
i •
j"
m
-•
-r
f
T
i
j
I
'T-
V
'L
i
i
*-
!
\t
_j
.!
?•/
»f
\
\
i
i
~i
I
i
'*/*
:'A
UHt .
'•nrrt
* :
»4 *•!*'» i
-Ut
1
Figure 6.1.3.3 Ozone Spectrum
6-6
-------
except for the vignetting factor resulting from the range. Again, signal
and noise observations are to be compared to the expected results.
6.2.1 Signal
Data for the San Diego field tests with the same conditions of slit height
and width setting, time constant, gain, Q, etc., as tttose used in the
laboratory tests are shown below.
v Slit Deflection V/Div S
' xs
2500 cm" 700 n X 2.7 mm l6.2 O.OU 0.65 volts
1000 cm"1 300 p. X 2.7 mm 6.5 " 0-26
The relative vignetting factor (An/Aft ) for the field test conditions,
(h = 9.3 mm), are as shovm below. The signal would be expected to be
reduced relative to the laboratory measurements by this ratio.
V
2500 cm
1000 cm
Afl /An
t' c
.68
.70
S Lab
xs
0.88 volts
0.36
Expected S
xs
0.60 volts
0.25
Thus, the observed field signals agree with those expected on the basis of
the laboratory measurements.
6.2.2 Noise
In general, two types of noise were observed: the zero line (presumably
electronic) noise and the noise associated with a signal. In some cases
the two values of noise were virtually equal and in other cases the signal
noise was substantially higher than the zero line noise.
An evaluation of the zero line noise was made by normalizing the observed
noise at the source lock-in amplifier output to the same gain and time constant
as that used in the laboratory tests, i.e., G = 10 and T = 0.01 seconds.
Data were taken either with the source beam blocked, at regions where the
filter cuts off or in regions where the flux is very low.
6-7
-------
/10 N / T
Vn eq. = Vn obsA G / V 0.01
The average value of V was about 0.3 to O.U volts peak to peak which
is about 2 times that observed in the laboratory.
No clear cut reason for this increase over the laboratory value is known.
Both the field and laboratory tests vere made using commercial line power.
The field test site was at times, rather windy, but no direct effect of the
wind on the zero line noise would be expected, except perhaps from cable
motion. It is curious that the zero line noise appeared to be a minimum
at about sunset (approaching the laboratory value).
The noise on the signal varied roughly with the signal indicating that
atmospheric refraction was the cause. During daylight hours with a large
slit width, this signal noise was substantially above the zero noise. Near
sunset with small slits the signal noise was much reduced. After dark with
even smaller slits the signal and zero line noise were approximately equal.
For the conditions of this test the signal noise became noticeably larger
than the zero line noise for slit widths greater than about 300 microns.
The increased signal noise limits the signal to noise ratio for the larger
slit widths.
The signal noise on the I/I- trace was more than that on the I trace, the
ratio being, in several instances, about twice that of the I trace. This
probably comes about partly because of the noise contribution of both I
and I (although the I signal noise is less than that of the I signal) and
partly because of a noise contribution of the I/I module for these signal
levels. 'The latter source of noise is reduced in the present instrument
because larger signals can now be used. At the time of these tests an overload
condition in the source compensation amplifier required low signal levels;
this condition has been corrected.
The tests described here were all run at a slit height of 2.7 mm for comparison
with laboratory data. It is believed that less signal noise may be obtained
with larger values of h, say h ~ h - 9.3 mm at O.U km, or even more. Tests
are planned to investigate the variation of signal noise with h/h . In any
case, signal noise will set a signal to noise limit for wide slit widths;
the question remains at what level of signal to noise. This will probably
6-8
-------
be an individual characteristic of each test site which may vary even
over the course of time during a day's testing.
The variations of atmospheric refraction which produce signal noise are a
property of the atmospheric path. Preliminary indications are that the
instrument response to these variations can be reduced for h < 12 mm, by
using a slit height greater than h . (Note, however,*that h = hQ should
still be used for calculating the ?lux in this case.) At the longest
ranges where h is about 1 mm, the use of a 12 mm slit height would permit
a considerable vertical image motion from atmospheric refraction with
little signal noise increase.
6.2.3 Typical Scans
Several typical scans made during the San Diego field tests are shown
on Figure 6.2.3.1.
6-9
-------
ii:i !-!;•!=!!:;; FH :rt:
:?•• r:? :i«^W;A 1 ••
liiiil!i!li!iil!i!llili!l!!l!lj3!lllB!ingi^
;~r 7 'if 'ifi " I—f.— II'.'
y^s 4>:
k«. « S t ::~:rr
^^^•:-"-
Wgurc 6.2.3.1 Typical Meld Test Scans
-------
7.0 MAINTENANCE
Most of the vendor provided equipment items in the ROSE system are
described in the manuals included as part of the system. No effort
is made to collect the trouble shooting and maintenance sections of
all these manuals here; rather, these manuals should T>e consulted
individually if trouble should develop in a particular vendor com-
ponent.
The main thrust of the discussion in this section is the trouble
shooting and maintenance of Convair built components and vendor com-
ponents for which manuals are not provided. For convenience, those
items for which manuals are provided are included with a notation of
that fact.
The components are divided into optical, mechanical, and electrical
groups.
7.1 OPTICAL MAINTENANCE
This section describes the recommended maintenance of the optical com-
ponents.
7 .;1.1 Blackbodie:;
There is no optical maintenance required for the blackbodies. The inner
surface of the cavities is coated v/ith a substance which can be damaged
by probing which, therefore, should be avoided.
A vendor manual for the blackbodies is provided.
7.1.2 Telescopes
The telescopes should not require optical, maintenance on a routine basis,
Cleaning should be done only when the surface becomes very badly con-
taminated since the infrared performance is much better than the visual
appearance usually indicates.
7-1
-------
Alignment of the telescopes requires a large collimated source and con-
siderable experience. Therefore, adjustments should not be made without
these essentials.
It is recommended that,for cleaning or realignment,the telescopes be returned
to the manufacturer, Perkin Elmer, Costa Mesa, California.
7.1.3 Reference Optics
The reference optics should need little maintenance aside from cleaning
and readjustment of the spherical mirrors if the monochromator mount is
relocated.
Cleaning of debris from the mirror surfaces can be done in many cases
sufficiently by blowing gently on the surface with a clean gas jet. A
more thorough cleaning might include the use of clean acetone to flood
the surface and blowing the acetone off the edge before it evaporates.
Collodion films may also be used to clean the surface by allowing the
collodion solvent to evaporate and stripping the film.
Alignment of the reference optical system may be done by placing a lamp
behind the entrance slit and aligning towards the blackbody or vice versa.
Each element is aligned in turn to center the beam on the next element. The
toroid should be rotated about the mount axis to change the symmetry of its
image. The toroid or diagonal should be adjusted so that the intermediate
focus passes through the center of the hole in the holder used for blocking
the reference beam.
Refer to Section U.2.6 for details of the reference chopper installation.
Refer to drawing 596-722-010 for details of the reference optical system.
7.1.14 Monochroraator
Optical maintenance of the monochromator should not be required. Since the
optical components are quite well protected, cleaning should not be necessary
on a routine basis.
7-2
-------
7.1.5 Detector Optics
The detector optics beinc enclosed should not require frequent cleanine-
U required, tte directions given under the Reference Optics secUon should
be followed.
Alignment of the detector optical system should be done with a strong visible
beam from the monochromator such as a mercury arc lamp or laser.
should be adjusted to.center the bean, on the diagonal. The diagonal may be
rotated in its mount to move the reflected i.age in the direction of the
length of the detector. Alignment tools are provided which, in use are p
top of the detector housing. One is used to position the image at thir t
focal point of the Cassegrain assembly before its m-tallatxon Th™*
is used to observe the image from the Cassegrain assembly at the Detector
location Use of these devices win position the components closely enough
so that all that is usually required is tweaking of the signal by P™^°j£^t
the dewar laterally and focussing the Cassegrain assembly (or what wor s a ou
as well, over a limited range is focussing the toroid). In the latter case,
however, use care not to distort the clips holding the toroid mirror in place.
Refer to drawing 596-722-011 for details of the detector optical system.
7.1.6 Detector
The principle maintenance task relating to the detector is its installation
on the cold head of the detector cooler. Orientation of «« detector, the
heater, and sensor for the temperature controller and the.hydrogen bulb lor
the vapor pressure thermometer are all shown on drawing 59o-722-Olo.
To remove the detector it is only necessary to remove the flange of the dewar
which contains the window, remove the mounting bolts and disconnect_the leads.
The leads are attached by means of O.OOU inch diameter Constantan wires, a
supply of which is provided in the detector cooler kit.
Also included is a supply of indium for making gaskets for all
mounted on the cold head. These should always be used to assure a good heat
transfer between the contact surfaces.
Although the detector is open within the dewar it should not be '^Jectedjo
contamination by opening the dewar while the detector is still cold, about
7-3
-------
3 hours is required for warmup. Should contamination occur, consult
with the manufacturer, Santa Barbara Research Center, Goleta, Calif.
7.1.7 Synch System
The synch system should not need optical maintenance.
The source synch details are shown on drawing 596-722-017 and reference
synch details are shown on drawing 596-722-010.
7.1.8 Alignment Device
The most probable maintenance task regarding the alignment devices is to
check or reset their settings. This was done initially as follows.
In the laboratory line up the source and receiver assemblies carefully
observing the images at the entrance slit and on the grating of the mono-
chromator. Place a source behind the entrance slit and observe it with
the bore-sight microscope at the source. Pig a temporary lamp and lens
on the eyepiece end of the boresight microscope.for the monochromator
so that the image of the lamp coincides with the crosshairs. Observe this
by means of another microscope looking in the objective end. A small
zirconium arc Point-o-lite was used but any small lamp will do. Then
place the monochrcinator boresight microscope into place and adjust its
diagonal so that the image falls in the same position in the field of the
boresight microscope at the source as that of the image of the entrance slit.
These images need not be centered; merely coincident. Repeat the procedure
at the opposite end using a small pinhole at the source as the target. Place
the lamp on the eyepiece end of the source boresight microscope and observe
it with the boresight microscope at the monochromator. Adjust the diagonal
of the source microscope until the target and .lamp image coincides.
The vide field di-x^'-i;^! cuttings arc not nearly so critical and may be set
using iitiy' convenient object eith'.-r in the laboratory or the field using the
boresight mcroscrjv-:.-s as a guide.
7.2 KSCHAKICAL MAINTENANCE
This section describes the rccoinmended mechanical maintenance.
-------
7.2.1 Stands
The stand maintenance consists mainly of lubrication of the wheels and
the screws on the front pads which should be required infrequently. The
screws have been lubricated with a dry graphite lubricant; oils or greases
should be avoided since they can hold abrasive material.
See drawing 596-722-006 for details of the front foot pads.
7.2.2 Auxiliary Stands
No mechanical maintenance is required.
7.2.3 Electronic Consoles
No mechanical maintenance is required.
7.2.U Telescopes
The only probable mechanical maintenance is the straightening or replacement
of taper pins used to align the telescope to the stand because of not removing
the telescope in a straight line. See Section U.2.5 for details of correcting
this situation.
Although there are screws by means of which the telescope shell can be removed
from the primary mirror cell these are not intended for normal disassembly
since to do so would undoubtedly change the telescope adjustment.
7.2.5 Reference Optical System
No mechanical maintenance is required other than possible bearing replacement
in the chopper or motor as indicated by roughness and noise. Refer to
drawing 596-722-010 for chopper details and Section U.2.6 regarding chopper
assembly. For the chopper ultra precise bearings should be used as specified
on the drawing. Use care not to damage the chopper blade or shaft during
removal and reassembly.
7.2.6 Monochromator
No mechanical maintenance is required except for a few drops of oil
infrequently in the wavenumber drive motor (the oil hole is on the bottom).
A vendor manual for the monochromator is provided.
-------
7.2.7 Detector Optical System
No mechanical maintenance is necessary.
7.2.8 Detector Cooler
Maintenance of the detector cooler should be required" only after extended
periods and is covered in the vendor manual provided.
7.2.9 Synch Systems
No maintenance is required.
7.3 ELECTRICAL MAINTENANCE
This section describes the recommended electrical maintenance.
7.3.1 Signal Sources
The Hg:Ge detector and synch detectors have been covered in Sections 7.1 and
7.2 and should require no electrical maintenance.
7.3.2 Signal Amplifiers
The preamplifier, the selective amplifier and the lock-in amplifier are
covered in vendor manuals provided.
The compensation amplifiers are described in detail in Section U.3.3 and
on drawing 596-722-027.
*
7.3.3 Data Acquisition System
The components within the lcx;ic box are of.two typvs: standard boardc
for which a vcr/lor manual J i; provided and Convair-tuilt boards which are
'described in Section U.3.5.
Tne control ..anol shoulu rcq.iire no electrical maintenance other than
possible noraal part replc-v^e-nt (such as switches) .
The bidirectional counter is covered in a vendor manual which is provided.
7-6
-------
The digital voltmeters are covered in a vendor manual which is
provided.
7.3.U Data Recording System
The electrical maintenance for the analog recorder, the digital printer,
the digital tape recorder and the data coupler is covered in vendor manuals
which are provided.
7.3.5 Power Sources
The ± 15 volt power source and the HIM BIN source are covered in vendor
manuals provided. The reference chopper and the ± 6 volt power supplies
are covered in Section U.3.8.
7.3.6 Fuse List
The following list of fuses used in the various components is given here
for convenient reference.
Component Fuse
Digital Voltmeter 5*103-015 £ Amp S1° B1°
Digital Voltmeter 5li03-010 £ Amp Slo Bio
Bidirectional Counter I Amp Slo Bio
Data Coupler \ Amp Slo Bio
Digitil Printer 3 Amp Slo Bio
Digital Tape Recorder 2 Amp Slo Bio
HIM BIN 3 Amp Slo Bio (2 required)
Reference Chopper Supply 3 Arap Slo Bio
Analog Recorder 1 Amp Slo Bio
Monochromator Drive 1 Amp Slo Bio
Blackbody Controller l| Amp Slo Bio and 15 Amp Slo Bio
Detector Cooler Temp Control f Amp Slo Bio
Blackbody Cooler 5 Amp Slo Bio
Thermocouple Gage IT Amp 3 AG
Source Chopper Drive 1 Amp Slo Bio
7-7
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