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PRELIMINARY DESIGN REVIEW REPORT (DRL Item MSM-S'- 137-2) 

ACQUISITION OPTICS SUBSYSTEM 

VOLUME I 

25 SEPTEMBER 1967 

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LEXINGTON, MASSACHUSETTS 02173 NEV 2 - 1967 

Subcontract No. 029B25000 

(preliminary dated 3 Jan 67) 

,t, ' 

ITEK CORPORATION 

Itek 

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PRELIMINARY DESIGN REVIEW REPORT (DRL Item MSM-S- 137 - 2) 

ACQUISITION OPTICS SUBSYSTEM 

VOLUME I 

25 SEPTEMBER 1967 

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SPECIAL FiANDLING --SEGRETT 

INTRODUCTION 

This preliminary design review report is presented in accordance 

with the requirements of specifications MSM-S-137-2 dated 14 August 

1967 and SCM-100A dated 12 September 1966 with the exceptions defined 

in Itek letters 9300-67-257 dated 8 August 1967 from Mr. A. L. Wright 

to Mr. J. E. Brogan and 9300-67-283 dated 15 September 1967 from 

Mr. W. N. Snouffer to Mr. J. E. Brogan. The report is organized in 

sections as tabulated in MSM-S-137-2. 

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SECRCT /SPECIAL HANDLING 

CONTENTS 

Volume I 

1.0 Acquisition Optics Design Compatibility With Specification 1-1 

1.1 General Description of Acquisition Optics 1-1 

1.2 Compliance With Specification 1-5 

1.2.1 Introduction 1-5 

1.2.2 Specification Requirement/Design Feature Comparison 1-6 

2.0 Compatibility of the AO With Other Equipment 2-1 

3.0 Selected Design Approach Integrity 3.1-1 

3.1 Error Budgets 3.1-1 

_3.2 Mass Properties 3.2-1 

3.2.1 Weight 3.2-1 

3.2.2 Gimbal Inertias 3.2-2 

3.3 Power Budget 3.3-1 

3.4 Reliability 3.4-1 

3.4.1 Reliability Program Status 3.4-1 

3.4.2 Reliability Figure of Merit Analysis 3.4-7 

3.4.2.1 Abstract 3.4-7 

3.4.2.2 Math Model for Telescope Reliability 3.4-8 

3.4.2.3 Calculation of Telescope Reliability 3.4-15 

, 4.3 Failure Mode and Effects Analysis 3.4-30 

3.4.3.1 Introduction 3.4-30 

3.4.3.2 Potential Critical Problems 3.4-31 

3.4.3.3 Potential Major Problems 3.4-32 

3.4.3.4 Compensations for Potential Problem Areas 3.4-34 

3.4.3.5 Life-Limited Devices 3.4-36 

3.4.3.6 Possible Safety Hazards 3.4-36 

3.5 Studies 3.5-1 

3.5.1 Protection Shroud 3.5-1 

3.5.2 Cont Angle 3.5-12 

3.5.3 Engineering Trade-Off Studies 3.5-14 

3.5.4 Miscellaneous Analysis 3.5-33 

3.6 Optical Design 3.6-1 

3.6.1 Design of Optics 3.6-1 

3.6.2 (Deleted) (Pages 3.6-55 Through 3.6-63 Deleted) 3.6-55 

3.6.3 Objective Lens Design Optimization 3.6-64 

3.6.4 Illumination Studies 3.6-76 

3.6.5 Fabrication and Alignment Tolerances 3.6-84 

3.6.6 Optical Transmittance 3.6-97 

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3.6.7 Optical Element Weights 3.6-108 

3.6.8 Redesign of Power Changer 3.6-115 

3.6.9 Interior Optical-Environmental Considerations 3.6-130 

3.6.10 Effects of Window and Objective Pressure Differentials 3.6-143 

3.6.11 Laboratory Module Atmosphere Effects on Optical Design 3.6-199 

3.6.12 Relationship Between Field Curvature and Off-Axis Performance 3.6-201 

3.6.13 Zoom Lens Type Trade Off 3.6-206 

3.6.14 Effect of Melt Deviations 3.6-208 

3.6.15 Window Thermal Analysis 3.6-211 

Volume II 3 

3.7 Tracking Pedestal Assembly 3.7-1 

3.7.1 Physical Description 3.7-1 

3.7.2 Design Parameters 3.7-1 

3.7.3 Structural Design 3.7-5 

3.7.4 Scanner Mechanical Design 3.7-268 

3.7.5 Scanner Electrical Design 3.7-491 

3.7.6 Scanner Thermal Design 3.7-498 

3.7.7 Scanner Assembly FMEA 3.7-564 

3.7.8 Summary 3.7-573 

Volume DI 

3.8 Fixed Fold Mirror and Mount 3.8-1 

8.8.1 Physical Description 3.8-1 

3.8.2 Structural Design Parameters 3.8-2 

3.8.3 Structural Design 3.8-4 

3.8.4 Thermal Design 3.8-154 

3.8.5 Fixed Fold Mirror FMEA 3.8-205 

3.8.6 Summary 3.8-206 

3.9 Protective Shroud 3.9-1 

3.9.1 Physical Description 3.9-1 

3.9.2 Design Parameters 3.9-3 

3.9.3 Structural Design 3.9-4 

3.9.4 Protective Shroud Drive 3.9-43 

3.9.5 Protective Shroud Electrical Design 3.9-81 

3.9.6 Thermal Design 3.9-83 

3.9.7 Shroud Reliability 3.9-115 

3.9.8 Summary 3.9-119 

Volumes IV and V 

3.10 Telescope Assembly 3.10-1 

3.10.1 Outer Tube Section 3.10-2 

3.10.1.1 Physical Description 3.10-2 

3.10.1.2 Design Parameters 3.10-2 

3.10.1.3 Structural Design 3.10-2 

3.10.1.4 Mechanical Design 3.10-194 

3.10.1.5 Thermal 3.10-265 

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3.10.1.6 Outer Tube Reliability 3 10-286 

3.10.1.7 Summary 3 10-287 

3.10.2 Intermediate Tube Assembly 3 10-288 

3.10.2.1 Physical Description 3 10-288 

3.10.2.2 Design Parameters 3 10-288 

3.10.2.3 Structural Design 3 10-288 

3.10.2.4 Power Changer Mechanical Design 3 10-308 

3.10.2.5 Magnification Change Electrical Design 3 10-380 

3.10.2.6 Thermal 3 10-383 

3.10.2.7 Low Power Assembly FMEA 3 10-401 

3.10.2.8 Summary 3 10-403 

3.10.3 Elbow Assembly 3 10-404 

3.10.3.1 Structural Design 3 10-404 

3.10.3.2 Mechanical Design 3 10-406 

3.10.3.3 Electrical Design of the Derotation and Blanking Drives 3 10-452 

3.10.3.4 Thermal 3.10-456 

3.10.3.5 Pechan, Blanking, and Cue FMEA 3.10-464 

3.10.3.6 Summary 3.10-476 

3.10.4 Eyepiece-Zoom Relay Assembly 3 10-478 

3.10.4.1 Structural Design 3.10-478 

3.10.4.2 Zoom Mechanical Design 3 10-635 

3.10.4.3 Zoom Mechanism Electrical Drive 3 10-662 

3.10.4.4 Eyepiece 3 10-665 

3.10.4.5 Peripheral Display 3.10-673 

3.10.4.6 Optical Filters 3 10-681 

3.10.4.7 Reticle 3 10-685 

3.10.4.8 Thermal 3 10-687 

3.10.4.9 Eyepiece-Zoom Relay Assembly FMEA 3 10-688 

3.10.4.10 Summary 3 10-690 

Volume VI 

4.0 Areas of Further Analysis 4-1 

5.0 Producibility of Selected Design Approach 5-1 

5.1 Introduction 5-1 

5.2 Other Related Sections 5-1 

5.3 Production Capabilities 5-1 

5.4 Inspection 5-3 

5.5 Special Tooling Requirements 5-5 

5.6 Test Equipment 5-9 

5.7 Test Facilities 5-9 

5.8 Standards and Processes 5-10 

5.9 Producibility of Selected Design Approach-Electro-Mechanical 5-21 

5.10 Producibility of Selected Design Approach-Optical 5-23 

5.11 Recommended Spares/Support Approach 5-79 

5.12 General Producibility Considerations 5-86 

6.0 Identification of Available Mockups, Breadboards, Models, etc. 6-1 

7.0 EMI and Integrated Test Plans 7-1 

7.1 Integrated Test Plan 7-1 

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7.2 EMI Control Plan 7-1 

7.3 Type I Documents 7-1 

8.0 Critical Part Specification 8-1 

9.0 Previously Released Hardware and Long Lead Items 9-1 

9.1 Introduction 9-1 

9.2 Released Hardware and Long Lead Items 9-1 

9.3 Major Long Lead Items Previously Released 9-29 

9.4 Released Hardware and Long Lead Items 9-31 

10.0 Schedule 10-1 

11.0 Baseline Documentation 11-1 

12.0 Supporting Documentation 12-1 

13.0 PDR Meeting Agenda 13-1 

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1.0 Acquisition Optics Design Compatibility with Specification 

1.1 General Description of the Acquisition Optics 

The Acquisition Optics Subsystem (AO) consists of a high power visual 

telescope used in conjunction with a precision pointing assembly for proper 

aiming of the telescope. The entire subsystem, consisting of two (2) identical 

sets of telescopes and pointing assemblies (a right-hand set and a left hand 

set) is mounted to the Lab Module section of the Manned Orbiting Laboratory 

(MOL) vehicle. The telescopes (Figure 1.1-1) are mounted within the Lab 

Module with the pointing assemblies (Figure 1.1-2),each consisting of a 

gimballed scanning mirror for pointing and a fixed folding mirror and window 

for directing the light from the scan mirror into the telescope, mounted 

externally on the Lab Module. 

The purpose of the Acquisition Optics subsystem is to enable the 

astronauts to examine a series of targets in order to assess the amount of 

military relevent activity in the target zone. The astronaut will evaluate the 

activity in the target area, make a priority determination to assist in the 

selection of target areas for photographic coverage by the main optical 

system, fine correct the tracking rates stored for the target in the onboard computer, and generally obtain real time reconnaissance information 

concerning the target. 

To fulfill the above objectives, the design of the AO was keyed to 

allowing the astronaut the maximum possible latitude in the use of the 

instrument. The scanner is able to point over a wide range in pitch 

(+70° to -40°) and in roll (+45° to -45°). A protective shroud 

covers the external elements when they are not in use. The zoom lens 

allows continuous magnification change from 127X to 63.5X and 31.75X to 

15.88X. The insertion of a two-element low power group provides the two 

power ranges noted. Since the field of view at lowest magnification is 

8 times that at highest magnification, the astronaut can select the amount 

of territory he wishes to have under surveillance at any one time. The 

apparent rotation of the scene is compensated by the use of a Pechan 

prism. A reticle is provided to aid in centering and tracking the targets 

in the field. Filters are provided for image contrast enhancement. The 

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eyepiece focusing device allows the telescope to be used by any astronaut with 

just a simple focusing adjustment. The peripheral display, seen at the edge 

of the apparent field, will provide the astronaut with time sequence and 

identification data to facilitate the decision making process. The derotation 

mechanism, zoom lens, low power groups, and blanking shutter have backup 

override controls which minimize the possibility of a catastrophic failure 

mode. A sun sensor and blanking 

shutter mechanism are provided to protect the astronaut should the scanner 

inadvertently point to the sun. This shutter mechanism may also be closed 

when the scanner is in a slewing mode in order to prevent the astronaut 

from experiencing an unpleasant physiological phenomenon. To aid the user 

in recognizing target areas, the ability for the telescope to accept a cue 

image has also been built into the system. 

In a typical operational sequence, the MOL system is launched for a 30 

day mission with the AO in a stowed configuration. Upon Lab Module activation, 

the crew removes the launch locks from the scanner gimbals, the protective 

shroud door, the low power groups, and the zoom lens. A brief functional 

checkout would follow. A typical surveillance pass would adhere to the 

following sequence: (a) the computer commands the scanner to slew to a 

target, (b) the observer checks the weather and general cloud cover in the 

target area, (c) he then searches the entire target field for other areas 

Iof interest in the vicinity of the pre-programmed target - if a more interesting 

target appears, he has the ability to override the preprogrammed list and 

can command the main optics to photograph the new area, (d) he identifies 

/and validates the target, e) he fine corrects the position accuracy and 

? !tracking rates and (f) he decides which target to photograph. Once the 

'decision on photography is made, he may then concentrate on extracting 

as much real time information as he can for the remainder of the target pass. 

The scanner is then slewed on command to the next target. 

Thus the Acquisition Optics subsystem performs two valuable tasks: 

examination of the field yields real-time reconnaissance data, and coupled 

with the main optical system it enhances the usefulness and quality of the 

reconnaissance photographs. 

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Fig. 1.1-1 — Mockup of AO subsystem telescope showing internal 

arrangement 

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Fig. 1.1-2 — Mockup of external components of AO subsystem (protective 

cover open) 

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1.2 Compliance with Specification 

1.2.1 Introduction 

Section 1.2 of the Preliminary Design Review Report (PDRR) satisfies the 

following documentation requirements: (a) Design Review Reports MSM-S-137-2, 

items 2, 5, and 6, and (b) Performance Analysis Report, GE-MOL-S-124. 

This section of the report examines the Acquisition Optics design and compares 

the design features with the specification requirements as set forth in Itek Specification 

No. 905850, Revision A, (Section 3.0). In those cases where the specification 

requirement is met, the analysis or drawing which verifies this fact is presented. In 

the event that the specification requirement is not met, the reason for the variation is 

stated, alternative design approaches are discussed, and a recommended course of 

action is described. 

The general organization of this section is as follows: the specification, Itek 

* 

No. 905850, Revision A, which is the document presently governing the Acquisition 

Optics design, is presented in its entirety in Addendum 1. 2-A, and each paragraph in 

this specification is then discussed in section 1.2.2. It should be noted that this is 

not a negotiated specification. Those portions of the specification where no exceptions 

were taken to the latest directed version of the design requirements (as expressed in 

EC-331B and SDR-137-4) are denoted by normal, Gothic-style print. Those portions 

where exceptions were taken are denoted by the words in italicized script. Also, portions 

which were deleted are shown by a - ( ) - symbol. The specification in Addendum 1. 2-A, 

exactly as it is stated, contains the Acquisition Optics design criteria which are presently 

being implemented and form the basis for the PDR. 

* All references to specification 905850 in the Preliminary Design Review Report refer 

specifically to Revision A of that specification contained in Addendum 1. 2-A. 

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SPECIAL HANDLING --SEGRE-T1.2.2 Specification Requirement/Design Feature Comparison 

Referenced paragraph numbers of specification 905850 are shown in parentheses 

following each section title. 

1.2.2.1 Performance (3.1) 

The Acquisition Optics Configuration Drawing, 114400 clearly shows that the 

component possesses the capabilities described in the above referenced paragraph 

without exception. These capabilities are discussed and analyzed in detail in later 

sections of this report. 

1.2.2.2 Optical Magnification and Field of View (3. 1. 1. 1. 1) 

The final optical design release, contained in Section 3.6.1 of this report, includes 

a discussion which shows that the requirements listed in the referenced paragraph are 

fully satisfied. 

1.2.2.3 Resolution (3.1.1.1.2) 

The latest resolution estimate for the component is 3.3 feet ground resolved 

distance. This estimate was calculated in the following manner. The modulation 

transfer function (MTF) for the highest lens magnification was taken from the final 

lens design release, section 3.6.1. The preliminary manufacturing and alignment 

tolerance budget for the component, as estimated in paragraph 3.6. 5, was used to 

degrade the lens MTF in order to produce a function which represents the completed 

system. This function was then intersected by the Schade visual resolution threshold 

function in order to estimate the resolution. Figure 1.2-1 shows the relationship 

between these functions and the parameters for which this calculation is valid. The 

requirements of the referenced paragraph are thus met without exception. The 

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justification for the use of the Schade threshold is as follows: 

a. A literature search is being conducted (see Figure 1.2. -2 for a threshold 

summary) and the preliminary results indicate that the Schade threshold with a 

minimum detectable modulation of 0.015 apparently yields realistic estimates of 

system performance. 

b. A discussion of this subject with experts in this field including Dr. S. Q. Duntley 

of the Visibility Laboratory on 14/15 June 1967 at SPO resulted in general concurrence 

to the use of this Schade threshold. 

Completion of the literature study and an experimental verification of performance 

prediction will be concluded in the near future. 

1.2.2.4 Scan Field (3. 1. 1. 1. 3) 

In order to allow line of-sight (LOS) pointing within the total field limits stated 

in the referenced paragraph, the appropriate scanner gimbal angles for a 9° cant angle 

were calculated. The results of these computations are presented in section 3.5.4. 

Drawing 905842 shows that the computed gimbal angles were used in the design of the 

scanner gimbal assembly. 

Figure 3.6.4-1 illustrates the fact there is no internal vignetting at the highest 

magnification. It is shown in subsequent design sections that there is no vignetting between 

the scan angles specified due to mirror and window sizes. However, further analysis is 

needed to determine if the scan mirror LOS intersects the LM contour. This analysis 

will soon be completed. 

1.2.2.5 Scanner Orientation (3.1.1.1.4) 

Compliance with the requirements of the reference paragraph cannot be determined at 

this time. The scanner gimbal axes orthogonality requirement of 0.5 arc minutes is well within 

the capability of theodolite alignment techniques (5 arc seconds . However, direction from 

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G. E. is required to establish, on the Mechanical Interface Con trol Drawing, the type 

of alignment means to be provided to satisfy the remainder of the requireme nts in the 

referenced paragraph. Once these alignment means are defined, an analysis will be conducted 

to determine the magnitude of the alignment adjustment capability which must be included in 

the design of the external AO hardware. 

1.2. 2. 6 Scanner Gimbal Acceleration (3. 1. 1. 1. 5) 

The scanner gimbal acceleration provisions in the referenced paragraph are 

satisfied without exception. Section 3.7.5.2 of this report discusses the scanner 

capabilities and shows that the requirements are met. 

1.2.2,7 Scanner Gimbal Torques (3.1.1,1.6). 

The design requirements of the referenced paragraph have been satisfied. 

Analyses showing these points are contained in section 3.7.4.2 of this report. 

Experimental verification of compliance will be demonstrated in the near future when 

bearing friction tests are run. 

Experimental determination of the Power Spectral Density (PSD) of the random 

torque variation will be conducted. The degree to which the design goal is achieved 

will then be estimated. 

1.2.2.8 Scanner Gimbal Inertia (3. 1. 1. 1. 7) 

The gimbal inertia requirements for the cross-roll and roll axes of no less than 

0. 08 and 0.36 slug-feet-squared respectively have not been satisfied. The actual values 

for the present design status are 0.054 and 0.21 slug-feet-squared for cross-roll and 

and roll respectively. Refer to section 3.2 for a detailed discussion of this problem 

area. 

1.2.2.9 Scanner Structural Dynamics (3. 1. 1. 1. 8) 

A preliminary scanner transmissibility analysis indicates that the provisions in 

the referenced paragraph will be met. The dynamic .analysis, presented in section 

3.7.3.3, treated only the structural contributions to the frequency response curve and 

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excluded gyro and torquer effects. In order to reaffirm the attainment of the specification 

requirements, tests will be conducted which include the gyros and torquers when these 

items are made available. 

1.2.2.10 Scanner Gimbal Position Readout (3. 1. 1. 1. 9) 

The requirements of the referenced paragraph will be met. Proof of this fact 

is presented in section 3.7.5.2 and in the purchase specifications for the encoder. 

(SK 114148 and SK 114149) Since the encoder manufacturer has agreed to the specification, 

the performance is expected to exceed the requirements in the referenced paragraph. 

1.2.2.11 Gimbal Stops (3.1.1.1.10) 

The design criteria in the referenced paragraph have been satisfied without 

exception. See section 3.7.4.3 of this report for a description of the stops. 

1.2.2.12 Image Rotation Capability (3. 1. 1. 1. 11) 

The requirements of the referenced paragraph are fully satisfied. Section 3.10.3.5 

of this report discusses the electrical design of the derotation mechanism and shows that 

these requirements are met. Figure 3.6.1-1 shows an optical schematic layout of the 

rotation device. 

1.2.2.13 Cue Insertion and Slew Blanking Provisions (3. 1. 1. 1. 12) 

The cue insertion provisions of the reference paragraph are satisfied. The 

target image cue image switch occurs in 0.4 second. The cue insertion mechanism is 

a separate device from the blanking mechanism. See section 3.10.3.2.3 of this report 

for a detailed description of the cue mechanism design. 

The slew blanking mechanism and solar blanking mechanism have been united 

into a single device. Since the reaction time for the solar blanking mechanism is more 

stringent (see specification paragraph 3.1.1.1.23) than 0.4 second time required by 

the slew blanking specification, this requirement is exceeded. The solar blanking time 

requirement, approximately 0.13 second has been used and the 

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mechanism is designed to satisfy that requirement. Refer to section 3.10.3.2.2 for 

more details. 

1.2.2.14 Telescope Design Approach (3.1.1.1.13) 

The final lens design release, section 3.6.1, clearly demonstrates that the 

provisions in the referenced paragraph are met without exception. 

1.2.2.15 Window (3.1.1.1.14) 

The component includes a window to allow light to pass into the aperture of the 

telescope. This window is shown in Figure 3.6.1-5. A study was conducted to prove 

that the window can withstand the pressure differentials present across the lab module 

(LM) structure without impairing optical resolution (see section 3. 6. 10). The results 

of this study show that the window can withstand the pressure differential s of the orbital 

environment without degrading the performance thus meeting the requirements of the 

referenced paragraph without exception. 

1.2.2.16 Aperture (3.1.1.1.15) 

The final lens design release, section 3.6.1, and the telescope configuration 

drawing SK 114400 demonstrates that the provisions in the referenced paragraph 

are met without exception. 

1.2.2.17 Eye Relief (3.1.1.1.16) 

The final lens design release, section 3.6.1, shows that the eye relief requirements 

are fulfilled without exception. The eye relief is 0.77 inch and the eye relief variations 

during zoom and power change are 0.02 and 0.001 inch respectively. 

1.2.2.18 Reticle (3.1.1.1.17) 

Section 3.10.4.7 shows that the component contains a reticle with the required 

pattern scribed on its surface. 

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1.2.2.19 Optical Filters (3.1.1.1.18) 

Section 3.10.4.6 shows the filter wheel with the four (4) sections for neutral 

density or spectral filters. Manual rotation of the wheel allows a crew member to 

select and insert the filter. The requirements of the referenced paragraph are, therefore, fulfilled. The types of filters to be inserted in the wheel are yet to be determined by 

the Contractor. 

1.2.2.20 Focus (3.1.1.1.19) 

A study was made to determine if a manual focus adjustment was required to 

refocus scenes corresponding to nadir distances between 70 nm and 230 nm. The result 

of the study was that the focus adjustment would not be required. This study also shows that the 

scene will remain in focus throughout the specified range of scan angles. The 

study results are contained in section 3.5.4.3. 

1.2.2.21 Zoom Optics (3.1.1.1.20) 

The final lens design release, section 3.6, shows the modulation transfer functions 

for the high and low power modes of operation, Figures 3.6.1-27 and 3.6.1-28. The 

specification requires that the resolution values for the various magnifications must be at 

least as good as a gradient which 

is simply the loss of resolution due to changing the magnification. In section 1.2.2.3, 

the resolution at the highest power is estimated to be 3. 3 feet. From the Figures 3.6.1-27 

and 3.6.1-28, it is seen that the transfer functions for the lower magnifications are all 

better than that for the highest magnification. Thus, the predicted resolution for these 

cases will be better than a prediction which is based on magnification change only. 

In other words, if the MTF' s for all magnifications were equal, then the provisions of 

the referenced paragraph would be met exactly. Since the lower magnifications have 

better MTF' s, the resolution estimates will be less than the values in the referenced 

specification paragraph, thus fulfilling the requirement without exception. 

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1.2.2.22 Zoom and Magnification Change (3.1.1.1.21) 

The requirements of the referenced paragraph are met without exception. 

Section 3.10.4.3 contains a discussion of zoom lens electrical design and 

section 3.10.2.4 and 3.10.2.5 a discussion of the power changer design. That 

the specification requirements are satisfied is also shown in these sections. 

1.2.2.23 Peripheral Display (3.1.1.1.22) 

The requirements of the referenced paragraph are satisfied with one exception. 

The luminous output requirement of the lamps is unspecified in the specification. 

Therefore, complete conformance to the specification cannot be determined. Section 

3.10.4.5 of this report contains a full description of the display and, shows 

compliance with the specification with the one exception stated above. 

1.2.2.24 Solar Blanking (3.1.1.1.23) 

The mechanism requirements of the referenced paragraph are satisfied by 

the slew/solar blanking device. See section 1.2.2.13 of this report for the 

discussion which justifies this conclusion. The sun sensor, which actuates the 

shutter, has yet to be designed. An optimization study which trades off considerations such as sensor location, weight, number of sensors for redundant coverage, 

etc. will be conducted. The result of this study will be a sun sensor design 

which fulfills the specification requirements. 

1.2.2.25 Environmental Shroud (3.1.1.1.24) 

The requirements of the referenced paragraph have been met with no exceptions. 

The exhaust impingement study (section 3.5.3.5) indicated that the shroud door would 

have to provide a positive seal. The design (section 3.9.4) incorporates a positive 

seal approach. The door opens fully in 10 seconds, thus exceeding the 25 seconds 

required by the specification. The shroud door fail-safe device, door position 

telemetry indication, and the redundant means to open the door in the event of a 

failure have been incorporated into the shroud design. Thus, section 3.9 demonstrates 

the achievement of the requirements in the referenced paragraph. 

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1.2.2.26 Pressure Integrity (3.1.1.1.25) 

The specification requirements in the referenced paragraph will be implemented. 

Analysis to determine the optimum vent design is being conducted. The results 

and design detail to date are in Section 3.10.1.4 Further work is required 

before this item will be satisfied. 

1.2.2.27 Launch Locks (3.1.1.1.26) 

Launch locks are required for the scanner gimbals, low power groups, the 

zoom lens, and the shroud door (sections 3.7.4, 3.10.2.4, 3.10.4.2 and 3.9.4 

respectively). In the detail design information sections for each of these 

assemblies, these locks are described and analyzed. The results of the analyses 

show that the requirements of the referenced section are met without exception. 

1.2.2.28 Alignment (3.1.1.2.1) 

No internal on-orbit alignment adjustments are required. The tracking mirror 

reflecting surface will be parallel to the cross-roll gimbal axis within 0.5 arc 

minutes. References defining the scanner axes to within(0.5 arc minutes will 

be provided as shown on the interface control drawing by mutual agreement. The 

provisions of the referenced paragraph are satisfied. 

1.2.2.29 Target Image (3.1.1.2.2) 

Figure SK 114400, the AO assembly drawing shows a monocular eyepiece, thus 

fulfilling the design requirement. 

1.2.2.30 Eyepiece Apparent Field of View (3.1.1.2.3) 

The final lens design release, section 3.6.1, shows that the apparent field 

of view is constant for all possible magnifications, thus fulfilling the 

requirement. 

1.2.2.31 Manual Overrides (3.1.1.2.4) 

The specification requirements for the override controls have been met with 

one exception. Section 1.2.2.44.3 indicates that the controls must be designed 

for use by a gloved hand. Until the gloved hand criteria are made available to 

Itek Corporation, compliance with this requirement cannot be ascertained. 
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1.2.2.31.1 Cue Insertion and Blanking Mechanism/s (3.1.1.2.4.1) 

The override control requirements in the referenced paragraph have been 

satisfied. See section 3.10.3.2 for design details. 

1.2.2.31.2 Zoom Mechanism (3.1.1.2.4.2) 

The zoom mechanism override control has been incorporated into the design 

of this subassembly. The requirements in the referenced paragraph are satisfied 

without exception. See section 3.10.4.2 for the detailed design. 

1.2.2.31.3 Magnification (Power) Change Mechanism (3.1.1.2.4.3) 

The override requirement for the power change mechanism is satisfied as 

shown in section 3.10.2.4 of this report. 

1.2.2.31.4 Derotation Mechanism (3.1.1.2.4.4) 

The requirement of the referenced paragraph is satisfied. Refer to 

paragraph 3.10.3.2 for design details. 

1.2.2.32 Scanner Gimbal Drive (3.1.1.2.5) 

The requirements of the specification are fully satisfied by the use of 

two independent stator windings in each torquer. Section 3.7.5 describes the 

scanner gimbal drive and shows in detail that these requirements are met. 

1.2.2.33 Scanner Gimbal Encoders (3.1.1.2.6) 

The requirements of the referenced paragraph, governing the encoder operational 

criteria, are satisfied without exception. This is shown in section 3.7.5 and 

the encoder specifications in SK 114148 and SK 114149. 

1.2.2.34 Scanner Gimbal Mounted Gyro Assembly (3.1.1.2.7) 

The gimbal-mounted gyro assembly was packaged with the scanner design, 

satisfying the requirements of the referenced paragraph. However, changes to 

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drawing 47D404663 47D404663 received on 19 September 1967, which include dimension and 

center of gravity shifts, require a redesign which is currently being analyzed. 

1.2.2.35 Instrumentation (3.1.1.2.8) 

The requirements in the referenced paragraph have been met without exception. 

The thermal instrumentation for the various parts of the AO is discussed in 

Addendum 1.2-E at the end of this section. 

1.2.2.36 Telemetry Input Signal Requirements (3.1.1.2.9) 

The requirements in the referenced paragraph have not been implemented pending 

the outcome of the uncertainty as to the voltage of the logic bus. The encoder 

will operate from +4.0 volts, but the telemetry requirements are based on a 5.0 volt 

logic bus. Therefore, either the telemetry signals should be referenced to 4.0 

volts or the encoder should operate from 5.0 volts. The specification requirements 

cannot be met until this question is settled by G.E. 

1.2.2.37 Optical Transmission Losses (3.1.1.2.10) 

The requirements of this paragraph have been satisfied. Refer to section 

3.6.6 for a detailed analysis of reflection and absorption losses in the 

telescope. The analysis shows that the transmission at the edge of the field 

is less than 1% smaller than it is at the center of the field and at the 1/2 

field position the transmissions are approximately equal. The axial system 

transmission at the high magnification is 35%. 

1.2.2.38 Field Breaks (3.1.1.2.11) 

The field breaks are described in sections 3.10.1.3 and 3.10.2.3. The 

locations are approximately 27 inches from the window for the first break 

and 29 inches further for the second break. This fulfills the requirement 

in the referenced paragraph. 

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1.2.2.39 Reliability (3.1.2.1) 

The requirements of the referenced paragraph are met with one possible 

exception. Section 3.4 of this report contains the reliability analysis of the 

component. 

The exception noted above is as follows: since the luminous output of 

the lamps in the peripheral display has yet to be determined, the MTBF for the 

lamps cannot be calculated. Therefore, the attainment of the MTBF requirement 

in the referenced paragraph cannot be proven. This analysis will be performed 

when the required display lamp luminance output is determined by G.E. 

1.2.2.40 Maintainability (3.1.2.2) 

The optical assembly is designed for ease of maintenance. The maintainability 

program described in Addendum 1.2-D demonstrates that all the maintainability 

requirements in the referenced paragraph are fulfilled. 

1.2.2.41 Useful Life (3.1.2.3) 

The reliability estimate in section 3.4 shows that the life and duty cycles 

contained in the referenced paragraph are achievable and, therefore, this requirement 

is satisfied with one exception. The luminous output of the peripheral display 

lamps has not been specified, and therefore, compliance with the specification, 

cannot be determined for this one case. 

1.2,2.42 Environmental (3.1.2.4) 

The design. triteria - in. the referenced paragraph are being utilized in the 

structural and environmental control design for the subassemblies in this component. 

The design details are presented throughout section 3.0. 

1.2.2.43 Transportability (3.1.2.5) 

The requirements of the referenced paragraph are fully satisfied. The design 

requirements for the shipping containers have been evaluated by a container manufacturer, 

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Container Research, Inc., and although they are felt to be stringent, the manufacturer 

states that they are achievable. 

1.2.2.44 Human Engineering Considerations (3.1.2.6) 

1.2.2.44.1 Field Flatness (3.1.2.6.1) 

The degree to which this design goal is achieved may be assessed from the 

study results presented in section 3.6.12. 

1.2.2.44.2 Exit Pupil and Eye Relief (3.1.2.6.2) 

The "AO Human Engineering Procedure" contained in Addendum 1.2-B outlines 

the human factors program being utilized in the design of the AO. With this 

as a basis, the degree to which this design goal is achieved can be assessed. 

1.2.2.44.3 Controls and Displays (3.1.2.6.3) 

Using the "AO Human Engineering Procedure" document (see Addendum 1.2-B) 

as a basis, all the manual controls in AO have been designed. These include the 

cue/slew/solar blanking mechanisms, filter wheel, focus adjustment and the override 

controls for the zoom, Pechan prism and low power groups. This fulfills one 

requirement in the referenced paragraph. Since the "Human Engineering Procedure" 

was written before the "gloved hand" requirement was known, the control designs 

have not incorporated this feature. When the details of the gloved hand control 

operation are made known to Itek Corporation, the manual control designs will be 

reviewed to assess the impact of this requirement and the designs will be 

updated accordingly. 

The ability to perceive the location of the control and the orientation of 

the particular device in order to utilize the control, in an ambient light level of 

0.1 foot candles has not been determined. A human factors analysis of this problem 

and a recommended design approach for its solution will be conducted in the near 

future. 

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1.2.2.45 Safety (3.1.2.7) 

The safety criteria set down in the referenced document will be met by the 

AO design. The "Safety Engineering Requirements" document, contained in Addendum 

1.2-C sets forth the procedures which will ensure that the AO design is totally 

safe for use by a human being. This specification requirement is met without 

exception. 

1.2.2.46 Interface Requirements (3.2.1) 

Refer to section 2.0 for a detailed discussion of the interface compliance 

with the specification. 

1.2.2.47 Component Identification (3.2.2) 

1.2.2.47.1 Government Furnished Property List (3.2.2.1) 

There is no requirement in the referenced paragraph. 

1.2.2.47.2 Contractor Furnished Property List (3.2.2.2) 

The scanner design is predicated on the assumption that the contractorfurnished items will be supplied and the design is ready to accept them. 

Procedures are also being written for the care and handling of these items 

prior to their inclusion in the finished component. This requirement is satisfied. 

1.2.2.47.3 Special Approval Components (3.2.2.3) 

The specification requirement is satisfied. Refer to section 8.0 for a 

list of the Special Approval components. 

1.2.2.48 General Design Features (3.3.1) 

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The Acquisition Optics Configuration Drawing, Figure SK 114400, clearly 

demonstrates that this component possesses all the design features required by 

the referenced paragraph. 

1.2.2.49 Weight (3.3.1.1) 

The current AO weight estimate is in section 3.2 of this report. This 

weight establishes the baseline in lieu of a requirement in the specification. 

1.2.2.50 Power (3.3.1.2) 

The latest AO power budget is contained in section 3.3 of this report. This 

power establishes the baseline in lieu of a requirement in the specification. 

1.2.2.51 Selection of Specifications and Standards (3.3.2) 

The requirements of the referenced paragraph are being satisfied without 

exception. 

1.2.2.52 Materials, Parts and Processes (3.3.3) 

The discussion in section 5.12.9 of this report shows that the specification 

criteria from the referenced paragraph are being satisfied without exception. 

1.2.2.53 Standard and Commercial Parts (3.3.4) 

The discussion in section 5.12.8 of this report shows that the requirements 

in the referenced paragraph are being implemented without exception. 

1.2.2.54 Moisture and Fungus Resistance (3.3.5) 

The requirements in the referenced paragraph are being implemented without 

exception. It will be shown that there are no materials in the AO design which 

could provide nutrients for a fungus growth as required by MIL-STD-454. Also, 

all surfaces in the AO will resist detrimental moisture effects through use of 

the materials, coatings and processes specified in MIL-S-5002. 

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1.2.2.55 Corrosion of Metal Parts (3.3.6) 

The discussion in section 5.0 of this report shows that the requirements in 

the referenced paragraph are being implemented without exception. Refer to section 

5.12.1 for a discussion of electrolytic corrosion control. Section 5.12.2 contains 

the stress corrosion control criteria. Section 5.12.3 details the protective 

treatment plan for the AO. 

1.2.2.56 Interchanegeability and Replaceability (3.3.7) 

The discussion in section 5.12.10 of this report shows that the requirements 

in the referenced paragraph are being implemented as much as is feasible. Cant 

angle and shroud requirements preclude interchangeable scanners. Interchangeable 

systems is also an impossibility after final alignment. The interchangeability 

and replaceability requirements are being carried out to the highest possible 

subassembly level. 

1.2.2.57 Workmanship (3.3.8) 

The workmanship standards in the referenced paragraph are being implemented. 

Refer to section 5.12.5 for a detailed discussion. 

1.2.2.58 Electromagnetic Interference (3.3.9) 

The provisions of the referenced paragraph are met. The "Electromagnetic 

Compatibility Control Plan" referenced in section 7.0 of this report details the 

procedures which will be followed in order to ensure electromagnetic compatibility 

with the rest of the system. 

1.2.2.59 Identification and Marking (3.3.10) 

The discussion in section 5.12.6 of this report shows that the requirements 

of the referenced paragraph are being implemented without exception. 

1.2.2.60 Storage (3.3.11) 

The discussion in section 5.12.7 of this report shows that the requirements 

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of the referenced paragraph are being implemented. The AO will perform as 

required after two year's storage in the specified environment. 

1.2.2.61 Cleanliness (3.3.12) 

The component will be assembled in a Class 10,000 clean room or shall be 

capable of being cleaned for use in a Class 10,000 area. See section 5.12.4 of 

this report for further details. 

1.2.2.62 Allowable Acoustic Noise (3.3.13) 

The requirements of the referenced paragraph will be implemented. Analysis 

of this problem will be conducted and the results will be applied to the design 

of those subassemblies which are sources of acoustic noise. 

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ADDENDUM 1.2- A 

Acquisition Optics 

System Design Specification 

Project 9300 

Specification No. 905850 

Revision A 

29 August 1967 

Description of Document 

This specification details the latest design and performance 

requirements for the Acquisition Optics subsystem. It is an amalgamation 

of the negotiated version of the specification (EC-331B; 3010-67-092/F), 

the Subcontractor Direction Record document (SDR No. 137-4; 9300-67-X187), 

and the changes which are still to be negotiated. These changes, which the 

project wishes to implement, are denoted by the italicized print. Deletions of requirements contained in the negotiated documents are denoted 

by a -0- symbol. 

This specification is the source of the design and performance 

requirements for the Acquisition Optics sybsystem and will be implemented 

accordingly. 

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Acquisition Optics 

System Design Specification 

Project 9300 

Section Title Page 

1.0 Scope 1 

2.0 Applicable Documents 1 

3.0 Requirements 6 

3.1 Performance 6 

3.1.1 Functional Characteristics 6 

3.1.1.1 Primary Performance Characteristics 6 

3.1.1.1.1 Optical Magnification and Field-of-view 6 

3.1.1.1.2 Resolution 6 

3.1.1.10 Scan Field 7 

3.1.1.1.4 Scanner Orientation 7 

3.1.1.1.5 Scanner Gimbal Acceleration 7 

3.1.1.1.6 Scanner Gimbal Torques 8 

3.1.1.1.7 Scanner Gimbal Inertia 8 

3.1.1.1.8 Scanner Structural Dynamics 8 

3.1.1.1.9 Scanner Gimbal Position Readout 8 

3.1.1.1.10 Gimbal Stops 9 

3.1.1.1.11 Image Rotation Capability 9 

3.1.1.1.12 Cue Insertion and Slew Blanking Provisions 9 

3.1.1.1.13 Telescope Design Approach 10 

3.1.1.1.14 Window 10 

3.1.1.1.15 Aperture 10 

3.1.1.1.16 Eye Relief 10 

3.1.1.1.17 Reticle 11 

3.1.1.1.18 Optical Filters 11 

3.1.1.1.19 Focus 11 

3.1.1.1.20 Zoom Optics 11 

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Acquisition Optics 

System Design Specification 

Project 9300 

Section Title Page 

3.1.1.1.21 Zoom and Magnification Change 11 

3.1.1.1.22 Peripheral Display 12 

3.1.1.1.23 Solar Blanking • 12 

3.1.1.1.24 Environmental Shroud 13 

3.1.1.1.25 Pressure Integrity 13 

3.1.1.1.26 Launch Locks 14 

3.1.1.2 Secondary Performance Characteristics 14 

3.1.1.2.1 Alignment 14 

3.1.1.2.2 Target Image 14 

3.1.1.2.3 Eyepiece Apparent Field of View 14 

3.1.1.2.4 Manual Overrides 14 

3.1.1.2.4.1 Cue Insertion and Blanking Mechanism/s 14 

3.1.1.2.4.2 Zoom Mechanism 15 

3.1.1.2.4.3 Magnification (Power) Change Mechanism 15 

3.1.1.2.4.4 Derotation Mechanism 15 

3.1.1.2.5 Scanner Gimbal Drive 15 

3.1.1.2.6 Scanner Gimbal Encoders 15 

3.1.1.2.7 Scanner Gimbal Mounted Gyro Assembly 16 

3.1.1.2.8 Instrumentation 16 

3.1.1.2.9 Telemetry Input Signal Requirements 16 

3.1.1.2.10 Optical Transmission Losses 17 

3.1.1.2.11 Field Breaks 17 

3.1.2 Operability 17 

3.1.2.1 Reliability 17 

3.1.2.2 Maintainability 17 

3.1.2.2.1 Maintenance and Repair 17 

3.1.2.2.2 Service and Access 18 

3.1.2.3 Useful Life 18 

3.1.2.4 Environmental 19 

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System Design Specification 

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Section Title Page 

3.1.2.4.1 Scanner, Folding Mirror, & Shroud 19 

3.1.2.4.2 Telescope 20 

3.1.2.4.3 Optical Window 20 

3.1.2.5 Transportability 21 

3.1.2.6 Human Engineering Considerations 21 

3.1.2.6.1 Field Flatness 21 

3.1.2.6.2 Exit Pupil and Eye Relief 21 

3.1.2.6.3 Controls & Displays 22 

3.1.2.7 Safety 22 

3.1.2.7.1 Flight Safety 22 

3.1.2.7.2 Ground safety 22 

3.1.2.7.3 Personnel Safety 22 

3.1.2.7.4 Explosive and/or Ordnance Safety 23 

3.2 Component Definition 23 

3.2.1 Interface Requirements 23 

3.2.1.1 Schematic Arrangement 23 

3.2.1.1.1 Scanner Electrical Interface 23 

3.2.1.1.2 Telescope Electrical Interface 23 

3.2.1.1.3 Shroud Electrical Interface 24 

3.2.1.2 Mechanical Interface Definition 24 

3.2.1.2.1 Scanner Mechanical Interfaces 24 

3.2.1.2.2 Telescope Mechanical Interface 25 

3.2.1.2.3 Window Mechanical Interface 25 

3.2.1.2.4 Shroud Mechanical Interface 25 

3.2.2 Component Identification 25 

3.2.2.1 Government Furnished Property List 25 

3.2.2.2 Contractor Furnished Property List 26 

3.2.2.3 Special Approval Components 26 

3.2.2.4 Logistics Critical Component List 26 

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Acquisition Optics 

System Design Specification 

Project 9300 

Section Title Page 

3.3 Design and Construction 26 

3.3.1 General Design Features 26 

3.3.1.1 Weight 27 

3.3.1.2 Power 27 

3.3.2 Selection of Specifications and Standards 27 

3.3.3 Materials, Parts, and Processes 27 

3.3.4 Standard and Commercial Parts 28 

3.3.5 Moisture and Fungus Resistance 28 

3.3.6 Corrosion of Metal Parts 29 

3.3.6.1 Electrolytic Corrosion 29 

3.3.6.2 Stress Corrosion 29 

3.3.6.3 Protective Tretatment 29 

3.3.7 Interchangeability and Replaceability 29 

3.3.8 Workmanship 30 

3.3.9 Electromagnetic Interference 30 

3.2.10 Identification and Marking 30 

3.3.11 Storage 30 

3.3.12 Cleanliness 30 

3.3.13 Allowable Acoustic Noise 30 

4.0 Quality Assurance Provisions 31 

4.1 Engineering Test and Evaluation 31 

4.2 Formal Qualification Tests 31 

4.2.1 Analyses Before Testing 31 

4.2.2 Test Conditions and Procedures 31 

4.2.3 Performance Verification Tests 31 

4.2.3.1 Dielectric Strength and Insulation 31 

Resistance Tests 

4.2.3.2 Corona and Arcing Test 32 

4.2.3.4 Scanner Structural Dynamics 32 

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System Design Specification 

Project 9300 

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4.2.3.5 Acceptance Test and Operability 

Demonstration 32 

4.2.4 Qualification Environmental Test 32 

4.2.4.1 Internal Components 32 

4.2.4.1.1 Acceleration 32 

4.2.4.1.2 Performance Test 33 

4.2.4.1.3 Vibration 33 

4.2.4.1.4 Performance Test 33 

4.2.4.1.5 Design Shock 33 

4.2.4.1.5.2 Performance Test 33 

4.2.4.1.5.3 Transportation Shock 33 

4.2.4.1.6 Performance Test 34 

4.2.4.1.7 Acoustic Noise 34 

4.2.4.1.8 Performance Test 34 

4.2.4.1.9 Temperature 34 

4.2.4.1.10 Performance Test 34 

4.2.4.1.11 Thermal Altitude 34 

4.2.4.1.12 Performance Test 34 

4.2.4.1.13 Oxygen Compatibility 34 

4.2.4.1.14 Helium Compatibility 34 

4.2.4.1.15 Performance Test 34 

4.2.4.1.16 Electromagnetic Compatibility 34 

4.2.4.1.17 Leakage and Pressure Integrity 34 

4.2.4.1.18 Endurance 35 

4.2.4.2 External Components 35 

4.2.4.2.1 Acceleration 35 

4.2.4.2.2 Performance Test 35 

4.2.4.2.3 Vibration 35 

4.2.4.2.4 Performance Test 36 

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Acquisition Optics 

System Design Specification 

Project 9300 

Section Title Page 

4.2.4.2.5 Shock Tests 36 

4.2.4.2.6 Performance Test 36 

4.2.4.2.7 Acoustic Noise 36 

4.2.4.2.8 Performance Test 36 

4.2.4.2.9 Thermal/Vacuum 36 

4.2.4.2.10 Performance Test 36 

4.2.4.2.11 Electromagnetic Compatibility 36 

4.2.4.2.12 Endurance 36 

4.3 Reliability Test and Analysis 37 

6.0 Notes 38 

10.0 Appendix 39 

VI 

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1.0 Scope 

This part of this specification establishes the requirements for 

performance, design, test, and qualification of one mission-design-series 

of equipment identified as optical assembly. This component is used to 

observe selected areas of the earth's surface from an orbiting vehicle in 

sufficient detail to detect activity of military interest. This equipment 

requires pre-aiming by means of computer direction and final aiming and 

tracking corrections by the operating observer. 

2.0 Applicable Documents 

The following documents, of exact issue shown, form a part of this 

specification to the extent specified herein. In the event of conflict 

between documents referenced here and the detailed content of Section 3, 4, 

& 10, the detailed requirement of Section 3, 4, & 10 shall be the superseding 

requirement. Any conflict between a document listed in this section and 

a lower tier referenced document shall be resolved in favor of the listed 

document. 

Specifications 

Military 

MIL-A-8421B Air Transportability Requirements, 

5 May 1960 Specification For 

MIL-C-26482C Connectors, Electric, Circular, 

Amend 1, Supp. lA Miniature, Quick Disconnect 

20 Feb. 1963 

MIL-E-25366C Electrical & Electronic Equip. & Systems, 

27 Feb. 1961 Guided Missiles 

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MIL-E-5400H Electronic Equipment, Aircraft, General 

Specification For 

MIL-F-7179B 

Amend 1 

29 July 1965 

MIL-H-27894A 

9 Jan. 1963 

MIL-S-38130 

10 Sept. 1963 

Finishes, Coatings, General 

Specification for 

Human Engineering Requirements for 

Aerospace Systems & Equipment 

Safety Engineering of Systems 

MIL-S-5002A Surface Treatments & Metallic Coatings 

Int. Amd. 1 *11* For Metal Surfaces 

24 Dec. 1963 

General Electric Company 

DR 1100A 

March 1967 

AN 1 Thru 4 

DR 1110A 

28 Feb. 1967 

DR 1112 Add. 1 

18 April 1966 

DR 1113 

18 April 1966 

Environmental Criteria and Component Test 

Requirements Specification - MOL 

Selected Ave Parts List 

Selected Processes for use in the MOL Mission 

Module, General Spec for 

Selected Structural Parts for Use in the MOL 

Mission Module, General Spec for 

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DR 1115 Selected Materials for use in the MOL Lab. 

Nov. 1956 and Specification for the MOL AGE/AAE 

DP 1690 

11 Nov. 1966 

S-30000 

18 Sept. 1964 

S-30001 

17 June 1963 

S-30002 

12 June 1963 

S-30029 

24 March 1965 

S-30042 

31 March 1966 

Standards 

Federal 

FED-STD-209 

16 Dec. 1963 

FED-STD-595 

Change 2 

19 Feb. 1962 

Electromagnetic Compatibility Requirements 

for MOL Program 

Design Requirements for Electronic Modules 

Module, Electronic, Metal Frame-Assembly, 

Instruction for 

Modules, Electronic, Encapsulated -CordwoodAssembly Instruction for 

Soldering Criteria for Microelectronic 

Devices. 

Engineering and Quality Standard 

Electronic Equipment. 

Clean Room & Work Station Requirements, 

Controlled Environments 

Colors 

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Military 

MIL-STD-130B 

Chg. 1 

7 Feb. 1964 

MIL-STD-143A 

Chg. 1 

14 May 1963 

MIL-STD-150A 

Chg. 2 

28 Jan. 1963 

MIL-STD-195 

Chg. 1 

20 Oct. 1965 

MIL-STD-202C 

Chg. 2 

27 May 1965 

MIL-STD-454A 

5 Jan. 1965 

MIL-STD-795 

Chg. 1 

26 Aug. 1964 

MIL-STD-803A 

1 Dec. 1964 

Identification Marking of U.S. Military 

Property 

Specs, & Stds., Order of Precedence 

Photographic Lens 

Marking of Connections for Electronic 

Assembly 

Test Methods for Electronic & Electrical 

Component Parts 

General Requirements for Electronic Equip. 

Colors 

Human Eng Des Crit For Aero & Equip. 

Part 11-Aero Sys Facil & Fac quip 

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MS-33586A Metals, Definition of Dissimilar 

16 Dec. 1958 

Drawings 

GE 711-00120 Temperature Envelope 

Bulletins 

ANA Bulletin 

400, Rev. U 

15 May 1964 

SP-63-470 Vol. 1 

SSD Exhibit 63-3 

24 June 1963 

Electronic Equipment, Aircraft & Guided 

Missiles, Applicable Documents 

Farada 

Engineering for Transportability 

MIL-HDBK-217A Reliability Stress & Failure Rate Data 

for Electronic Equipment 

MIL-HDBK-141 

5 Oct. 1962 

Technical Order 

WADC-TR52-321 

PIR No. 7223410L-278 

Military Standardization Handbook 

Optical Design 

Anthropometry of Flying Personnel 

DOD Index of Specifications and Standards 

Special Subsystem Design Load Factors 

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3.0 Requirements 

3.1 Performance 

The optical assembly consists of a scanner, folding mirror, and 

shroud externally mounted to an orbiting vehicle, an optical window in the 

vehicle skin, and an internally mounted telescope. The assembly in 

conjunction with on-board computer and/or crew initiated command & control 

provides acquisition and tracking of selected targets. A means for 

actuation of magnification, image rotation, and focus shall be provided. 

The telescope allows insertion of externally provided image cue projection 

and provides means for switching between scanner and cue images. The image 

switching mechanism or a separate mechanism also provides blanking of the 

target image on command. The optical assembly design incorporates spectral 

and/or neutral density filters. -0-, 

3.1.1 Functional Characteristics 

3.1.1.1 Primary Performance Characteristics 

3.1.1.1.1 Optical Magnification and Field-of-view 

Two ranges of optical magnifications shall be provided. In the 

high range, magnification shall be continuously variable from the maximum which 

shall be 127x plus or minus 5x to at least one half of maximum magnification. 

The maximum magnification in the high range shall provide a real field of view 

0.5 plus or minus 0.03 degrees in diameter. ›- The exit pupil diameter at maximum magnification shall be no less than 2.0 mm. The minimum magnification 

in the low range shall be no greater than 16x plus or minus lx and shall provide 

a real field of view of no less than 4 degrees. The exit pupil diameter 

in this case shall be at least 4 mm. Fon ate magniiications, a pontion oi 

the gad (14 view mat be ofmcmed by the duo play descitibed in patagAaph 3.1.1.1.22. 

A continuous zoom between minimum magnification and twice minimum magnification 

shall be provided. 

3.1.1.1.2 Resolution 

The on-axis resolving power of the acquisition optics shall enable 

a flight crew member,-0- to resolve a 3-bar target corresponding to that specified 

in MIL-STD-150A, of 1.65 foot wide white bars oriented in any direction with 

1 .65 foot spacing on a black background (3.3 foot per line pair). This 

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acquisition optics resolution shall be obtainable when 

A. The apparent contrast ratio of the 3-bar target, as seen 

by the acquisition optics aperture is 2 to 1. 

B. The apparent scene brightness, as seen by the acquisition 

optics aperture, is 530 foot-lamberts. 

C. The line-of-sight range to the target is 80 N. mi. 

D. The required resolution shall be obtained at maximum magnification 

3.1.1.1.3 Scan Field 

The scanner shall permit LOS pointing within a total field of 

view of plus 70 deg. forward to minus 40 deg. aft in cross roll, and plus' 

or minus 45 deg. in roll, referenced to the orbiting vehicle coordinates. 

There shall be no vignetting or obscuration between plus 40 degrees and 

plus 10 degrees in pitch, at roll angles within plus or minus 35 degrees 

cross track at the highest magnification, referenced to the orbiting vehicle 

coordinates. See Figure 1. 

3.1.1.1.4 Scanner Orientation 

The scanner roll and cross roll gimbal axes shall be orthogonal 

within plus or minus 0.5 arc min. The scanner shall be designed to allow 

installation so that the optical axis between the scanner and the folding 

mirror is parallel to the vehicle roll axis. The scanner roll axis shall 

be capable of being aligned such that, 

A. It is 9 degrees plus or minus 3 arc minutes frcm the 

vehicle roll axis in the pitch roll plane 

B. It lies in the vehicle roll pitch plane within plus or 

minus 1.0 arc minutes. 

Means shall be provided to permit measurement of the actual scanner roll axis 

alignment -()- to an external reference. The direction of cant for scanners can 

be opposite to each other, the direction chosen to be compatible with envelope 

and obscuration constraints. See Figure 2. 

3.1.1.1.5 Scanner Gimbal Acceleration 

The scanner shall be capable of roll accelerations of at least 

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2 rad/ sec. sq. and simultaneous cross roll acceleration of at least 1 

rad/sec. sq. The full roll acceleration capability shall be attainable in 

LOS scan range of plus or minus 40 degrees (with respect to the vehicle 

coordinates) a fall off in acceleration capability of 10% shall be tolerated 

in the remainder of the roll scan range defined in paragraph 3.1.1.1.3. 

The full cross roll acceleration capability shall be attainable in the cross 

roll range defined in paragraph 3.1.1.1.3. 

3.1.1.1.6 Scanner Gimbal Torques 

The mean value of the running friction torque for either gimbal 

shall be no greater than 2 in-oz. Starting friction torque shall be no greater 

than 1.5 times the mean value of running friction torque for each gimbal. 

1 A4 a design goat, the power spectral density of the random torque variation 

about the mean value of running friction shall be completely enclosed by 

the PSD curve of Figure 3. The torque tolerances shall be satisfied for LOS 

velocities of 0.1 to 3.5 deg/sec in cross roll and 0.02 to 0.15 deg/sec in 

roll. 

3.1.1.1.7 Scanner Gimbal Inertia 

The cross roll gimbal inertia shall be no less than 0.08 slug 

foot squared and the roll gimbal inertia no less than 0.36 slug foot squared. 

3.1.1.1.8 Scanner Structural Dynamics 

The structural dynamics of the scanner assembly, scanner assembly 

mount, gyro assembly mount and mount location shall be such that the frequency 

response of each axis of the gyro output signal to motor excitation, normalized ___ 

to the response at 1 rad/sec and compensated for the motor electrical time 

constants and the gyro transfer function shall have no amplitude excursions 

above the profile of Figure 4. 

3.1.1.1.9 Scanner Gimbal Position Readout 

A. For each scanner axis, an incremental position shall be 

provided which shall permit, by counting, the measurement of 

gimbal position. The mean error of these position measurements 

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shall be not more than 10 arc seconds, where the error is defined as the difference between the encoders output and the 

true gimbal position. /6' 

B. The power spectral density of the random components of the 

position error shall fall within the envelope of Figure 5. 

CW.t_cco 

These performance requirements for A and B above shall be met 

for cross roll gimbal rate of plus or minus 40 deg/sec to plus or minus 

0.10 deg/sec, and roll gimbal rate of plus or minus 50 deg/sec to plus or 

minus 0.02 deg/sec. 

3.1.1.1.10 Gimbal Stops 

Mechanical stops and energy absorbers shall be provided at the 

extremes of roll and cross roll gimbal travel to preclude damage to the 

scanner in the event of a worst case failure which causes a constant 28.0 

VDC to be applied to the torque motor terminals. The gimbal stops shall 

allow for a 1.5 degree travel in excess of the scan field requirements 

of 3.1.1.1.3 prior to contacting the stop. 

3.1.1.1.11 Image Rotation Capability 

Image rotation capability shall be provided over a range of 

plus or minus 50 degrees in response to electrical commands. Electrical 

indication of rotation shall be provided which shall have an accuracy 

of 0.5 degrees, 2 sigma. and a resolution of no less than 0.175 degree. 

Maximum image rotation velocity shall be no less than 60 deg/sec with an 

acceleration capability of not less than 2 rad/per sec sq. 

3.1.1.1.12 Cue Insertion and Stew Btanking P4ovizion4 

The telescope shall accept an externally-provided cue image 

into the optical assembly for display through the eyepiece. The design 

shall provide for routing either the target image from the scanner or the 

externally-provided cue image to the eyepiece. Switching from one image 

to the other shall be accomplished in less than 0.4 seconds after the 

;'j application of power to the drive motor. The, optical aszembty Acta 

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include a 4huttet which witt cpmpteteiy btank the target image Oom the 

4Caletet in teAA .than 0.4 4econd6 atitet the apptication oti power to the 

drive motors. Reatotation ob the target image to the eyepiece 4hatt be 

completed in te,44 than 0.4 zeconda agen apptication oi power to the 

dtive motot. It shatt be peArnazibte to satisliy the above nequiumenta 

with a 4ingte mechani4m. Ptovi4ion4 Ahatt be made eon bait babe 4n the 

target b&tniz position. An electrical indication of the position of the 

cue device in each position shall be provided. 

3.1.1.1.13 Telescope Design Approach 

The telescope shall employ a refractive objective lens and 

shall be corrected over the visible wavelength region according to the 

spectral response characteristics of the eye as defined in Section 4 of 

MIL-HDBK-141. 

3.1.1.1.14 Window 

The optical design shall include a window. This window is in 

the optical path of the telescope and serves as a boundary between the 

exterior and interior of the vehicle and through which passes light from 

the target. The window shall support the pressure differentials present 

across the lab module structure without degrading optical resolution 

beyond the limits defined in this specification. 

3.1.1.1.15 Aperture 

The limiting aperture of the telescope in the high magnification 

range shall be the objective lens. Its unobscured diameter shall be at least 

10 inches. The limiting aperture in the low magnification range shall be compatible with the requirements of 3.1.1.1.1. 

3.1.1.1.16 Eye Relief 

The eyepiece relief shall be at least 0.40 inch. The eyepiece 

relief shall not vary by more than 0.060 inches throughout the entire range 

of magnification specified. 

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3.1.1.1.17 Reticle 

A nonilluminated circular reticle shall be provided as shown in 

Figure 6. 

3.1.1.1.18 Optical Filters 

A set of four spectral or neutral density filters shall be 

provided as part of the optical assembly. Selection and insertion of a 

filter shall be at the option of crew member. 

3.1.1.1.19 Focus 

If necessary for focusing of scenes corresponding to nadir 

distances between 70 & 230nm, a manual focus adjustment shall be provided. 

The scene shall remain within the focusing accommodation of the eye 

throughout the tracking scan angles specified in paragraph 3.1.1.1.3 

without adjustments. 

3.1.1.1.20 Zoom Optics 

Zoom operation and the resulting change of magnification shall 

not degrade on-axis resolution undet conditions "A" thitough "D" ob paragraph 

3.1.1.1.2 beyond the limits of an envelope defined as follows: a straight 

line on log-log paper, between coordinates, 

High Power Low Power 

Ground Resolution, in feet 3.3 6.6 13.2 26.4 

Magnification 127.0 63.5 31.75 15.88 

Radial position displacement during zoom shall not compromise system 

performance, as defined in the above envelope. 

3.1.1.1.21 Zoom and Magnification Change 

7 4% P 

The zoom assembly shall be electrically actuated. The full , 

, ,/ zoom range shall be covered in 1.0 seconds when the maximum position change 

command is applied. An electrical signal representing zoom-magnification 

without discontinuity shall be provided with an accuracy of 2.0% of full range. 

The magnification change assembly shall be electrically actuated. Magni- 

/ fication change shall take place in no more than 1.0 seconds. An electrical 

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Signal shall be provided to indicate the status of the magnification 

assembly in either the high or low magnification position. 

3.1.1.1.22 Peripheral Display 

An illuminated display shall be incorporated in the telescope 

design. The display shall be designed so that its patterns are visible 

within the eyepiece field of view and the display shall obscure no more 

than 5 degrees at the periphery of the apparent field of view. The 

peripheral display shall consist of 35 illuminated dots having the design 

characteristics and geometric arrangement requirements described herein. 

The source light of each dot shall be individually controllable -on-offfrom an external source. The light sources shall be designed to permit the 

4ratti-tames. of all sources to be continuously controllable via a single control 

up to MD soot-eandte6,, Figure 7 illustrates the dot pattern. The tamps 

of the peripheral display shall be tang's-ten 4itamentz. The COt0AZ q the 

dot loattetn4 cVte at4o shown in FiguAe 7. 

3.1.1.1.23 Solar Blanking 

A blanking mechanism shall be provided for solar protection. 

The mechanism shall consist of a shutter to blank the sun from the eyepiece 

and a sun sensor to detect the proximity of the solar vector to the LOS. 

General Electric will provide all associated electronics. 

A. The mechanism shall be capable of fully blanking the fov 

before any portion of the solar disk appears in the fov 

when the rate of closure between the optical assembly line 

of sight and the solar vector is equal to or less than 

110 degrees/sec. The placement of the blanking stop in the 

system shall be such as to prevent damage to the astronauts 

eye or to the optical assembly. 

The reaction time of the electronic circuitry may be neglected 

by the Subcontractor in meeting the requirements of this paragraph. 

B. The mechanism shall not blank the fov when the LOS is more 

than 15 degrees from the solar vector. 

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C. The cue insertion mechanism may be used for blanking if feasible 

in the light of the requirements of this paragraph. 

3.1.1.1.24 Environmental Shroud 

A protective shroud protecting the scanner, window, and folding 

mirror shall be provided which shall fit within, and be compatible with the 

aerodynamic fairing which is required during powered flight and which is 

jettisoned prior to orbital insertion. The aerodynamic and heating toad's 

expetienced between the o4 bct,ihing ejection and otbitat imeAtion wte 

tezz 4evete than OA noArnat onbitae opetation4. 

When in the launch or stowed position, the maximum protrusion 

of the shroud shall not exceed 15.65 inches from the exterior radiator surface of the lab module. The protectiveshroud shall contain an electrically 

actuated door which, when closed, shall provide protection for the scanner 

assembly, window, and folding mirror from exhaust products of the orbital 

maintenance thrusters and from the water, which the output of the waste 

management system. The door shall travel from the closed position to the 

fully open position or from fully open to closed inc25 seconds maximum on 

receipt of the appropriate signals supplied by others. The door shall be designed to fail safe in the open position. Electrical signals to indicate the 

fully open or fully closed door position shall be provided. Redundant means to 

open the door shall be provided. 

3.1.1.1.25 Pressure Integrity 

The telescope shall be designed such that the space between objective lens and window will be vented at a cant/Lotted tate to and from the 

telescope. -()- Flow from telescope to objective lens/window space shall not 

exceed 100 cc/daygineat inch ob zea2 got a hetium atomospheu at 70° F when 

the pressure differential across the objective lens 4:4 5 PSIA. The telescope 

shall be designed for operation in the LM with pressure of 5.0 plus or minus 

0.2 PSIA, either 30% helium and 70% oxygen or pure oxygen. 

It shall withstand LM depressurization from liftoff pressure of 19.0 

PSIA maximum to on-orbit pressurization of 5.0 plus or minus 0.2 PSIA at a LM 

pheosm.ization Aate not to exceed 0.5 oiRecond. The venting shall. ptovide 

bon pte44ute equalization 4uch that the AO wLU be opeAationat £n no mom. 

than 6 hou'us atiten taufick-der/trzzwu zet6L-er t. 

It shall also withstand two LM depressurization and repressurization 

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events (to orbiting vehicle ambient pressure 10-9 Torr) of up to four hours 

each. The venting 4hatt ptovide son piteisAtae equaiization such that the AO 

w112 be opexationat in no more, than 3. hound abten AepuzAmization. 

3.1.1.1.26 Launch Locks 

Launch locks shall be provided for any mechanical moving parts 

if required to sustain the powered flight environments of paragraph 3.1.2.4. 

Telescope launch locks, if required, shall be designed for manual removal 

or deactivation. Scanner launch locks, if required, shall have a remote 

redundant means of removal or deactivaiton. 

3.1.1.2 Secondary Performance Characteristics 

3.1.1.2.1 Alignment 

References defining the scanner axes to within plus or minus arc 

minute are to be provided on the scanner to permit optical alignment during 

installation. No on-orbit internal alignment adjustment of the optical 

assemblies shall be required. The tracking mirror reflecting surface shall 

be parallel to its cross-loll gimbal axis within plus or minus 0.5 arc minute. 

3.1.1.2.2 Target Image 

The target image shall be presented through a monocular eyepiece 

lens assembly. 

3.1.1.2.3 Eyepiece Apparent Field of View 

The apparent field of view of the eyepiece shall be the same for 

both magnification ranges and throughout the zoom range. 

3.1.1.2.4 Manual Overrides 

3.1.1.2.4.1 Cue Insertion and Blanking Mechanism/s 

The cue insertion/blanking mechanism/s shall be provided with a 

manual override which enables a crewmember to manually remove the cue insertion/ 

blanking devices from the optical path between the target scene and eyepiece. 

This will be an operation in the event of a controle signal or mechanism 

failures which prohibit display of the target image. 

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3.1.1.2.4.2 Zoom Mechanism 

The zoom mechanism shall be provided with a manual override 

which enables a crewmember to manually change from low zoom to high zoom 

or vice versa in the event of control signal or mechanism failure. Manual 

positioning of the zoom at intermediate powers is desirable, but not 

mandatory. 

3.1.1.2.4.3 Magnification (Power) Change Mechanism 

The magnification (power) change mechanism shall be provided 

with a manual override which enables a crewmember to manually change from 

low power to high power and vice versa in the event of a control signal 

or drive motor failure. 

3.1.1.2.4.4 Derotation Mechanism 

The derotation mechanism shall be provided with a manual override and index which enables a crewmember to manually position the Pechan 

prism within plus or minus 5 degrees of the neutral or central position in 

the event of a control signal or drive motor failure. 

3.1.1.2.5 Scanner Gimbal Drive 

Each gimbal shall be activated by one or two brushless, noncommutated motors. If one torquer is used, two independent stator windings shall 

be provided for each gimbal, each of which shall be capable of driving its 

associated gimbal at one-half the acceleration specified in paragraph 3.1.1.1.5 

in the event of any failure in the other winding. 

3.1.1.2.6 Scanner Gimbal Encoders 

Each scanner gimbal shall be provided with an incremental encoder 

with a resolution of 1 part in 2 to the 20th power for roll and 1 part in 2 

to the 18th power for cross roll. The encoders and mounting procedures 

shall be compatible with the scanner gimbal readout requirements of paragraph 

3.1.1.1.9. In addition to the incremental position data, the encoders shall 

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provide two auxiliary signals, one to indicate the CW and CCW limits of gimbal 

travel and the zero reference position, the second signal to indicate whether 

the gimbal is CW or CCW from the zero reference position. 

3.1.1.2.7 Scanner Gimbal Mounted Gyro Assembly 

A gyro assembly, consisting of a rate gyro package, -()- electronic 

assembly -()- and an interconnecting cable shall be mounted on each gimbal. The 

gyro assemblies shall be furnished by the Contractor. The Subcontractor shall 

provide the cabling from the gyro assemblies to the penetration connector ■ as 

shown in Figure 10. Physicat 6 theAmat spec“ication4 tiot the 9y/to 04emb.ty 

wte inctuded on the inteqace contito-e ditatu:ng. 

3.1.1.2.8 Instrumentation 

Thermal instrumentation, sensors, and associated harnesses 

shall be provided on the optical assembly as required -()- by the Subcontractor. 

3.1.1.2.9 Telemetry Input Signal Requirements 

Any signals supplied to the PCM telemetry system shall have the 

following parameters. 

A. Analog Signals 

1. Voltage range - 0.0 to 5.0 VDC 

2. Signal output impedance 10,000 ohms max. 

3. Multiplexer input impedance- 10 megohms min. 

B. Discrete event signals and multiple bit binary word signals 

1. Voltage Levels 

Binary one plus 4.5 plus or minus 1.0 VDC 

Binary zero plus 0-.25 plus or minus 0.25 VDC 

2. Signal Source Impedance 

Binary one 10,000 ohms max. 

Binary zero 500 ohms max. 

3. Signal Conditioner Input Impedance 

Binary one 50,000 ohms min. 

Binary zero 3,000 ohms min. 

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3.1.1.2.10 Optical Transmission Losses 

The transmission losses of the optical system as viewed by the 

crew shall be minimized. Within the scan angles which have no vignetting or 

obscuration and with uniform scene brightness, the transmissions at the edge of 

the apparent field of view shall be at least one-half that at the center. 

At half the distance between the edge and center, the transmissions shall be 

at least 0.8 of that at the center. The system transmission shall be at least 

25%. 

3.1.1.2.11 Field Breaks 

To facilitate installation, the telescope shall be designed with 

two field breaks. The first break shall be approximately 27 inches from the 

window inner surface and the second shall be approximately 29 inches further, 

measured from the first break. 

3.1.2 Operability 

3.1.2.1 Reliability 

The optical assembly shall have a MTBF of at least 11,600 hrs., 

exclusive of the rate gyros and peripheral display lamps, where a failure 

is defined as the inability to perform in accordance with the requirements 

of this specification. The 35 lamps shall have an MTBF of 46,300 hours. 

Cyclic operation is as defined in paragraph 3.1.2.3 of this specification. 

3.1.2.2 Maintainability 

The optical assembly shall be designed for ease of 

maintainability to minimize equipment down time during prelaunch conditions. 

3.1.2.2.1 Maintenance and Repair 

During orbital operation there shall be no periodic maintenance. 

The optical assembly shall be designed to minimize the need for routine main- 

_ tenance during the entire service of the end item. The design shall not 

preclude the performance of simple maintenance of the telescope by the astronaut 

during orbital operation. 

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3.1.2.2.2 Service and Access 

On-orbit crew access shall be considered in the design of focus 

adjustment and manual override controls. Modular packaging shall be used 

wherever possible. Ready access to various parts to simplify inspection, 

servicing, and replacement shall be considered in the design of the optical 

assembly. 

3.1.2.3 Useful Life 

The optical assembly shall be capable of operating within a duty 

cycle of 7% on 93% off in accordance with the requirements of this specification, for a minimum of 7000 hours (490 hrs. on, 6510 hrs. off)during a 

total useful life of 5 years as required by any combination of the following: 

A. Transportation limited to 60 days as defined in DR1100, 

paragraph 3.1.2.1. 

B. Storage per paragraph 3.3.11 of this specification 

C. Handling, assembly, and checkout 9 month maximum, as 

defined in DR 1100, paragraph 3.1.2.3. 

D. Prelaunch phase 13 months, as defined in DR 1100, paragraph 3.1.2.4. 

E. Launch and ascent 10 minutes, as defined in DR 1100, 

paragraph 3.1.2.5. 

F. Orbital operation a minimum total of 720 hrs., 50 hrs. on, 

670 hrs. off with a duty cycle of 1 to 25 minutes on 

and up to 12 hrs. off. 

The optical assembly shall be designed for the following minimum 

operations during a 30 day on orbit mission 

Gimbal slews and tracks 12,000 

Magnification (power) changer (in-out) 3,000 

Zoom positioning 6,000 

Blanking cycles (in-out) 12,000 

Prism positionings 12,000 

Protective Shroud Door 500 

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3.1.2.4 Environmental 

This component shall be designed to withstand the environmental 

conditions specified in GE specification No. DR 1100 as defined below. The 

component shall operate during portions of handling, assembly and checkout, 

prelaunch, and within the duty cycle of paragraph 3.1.2.3 of this specification when on orbit. The component does not operate during the other 

mission phases. 

The optical assembly shall be designed to operate within an orbit 

envelope as defined by Figure 11. The specified nominal orbit is 80 nm perigee, 

— 180 nm apogee. Perigee will occur at 55 degrees N. latitude on the sun 

illiminated side of the earth. The included angle between the earth-sun 

line and the orbit plane shall vary between plus 60 and minus 60 degree. 

Thermal doors and sun shields shall be provided as necessary to satisfy 

the specified optical assembly performance requirements. The optical assembly 

shall be designed to preclude performance degrading contamination of the 

optical elements from orbit maintenance nozzle exhaust products and waste 

management waken. products. 

3.1.2.4.1 Scanner, Folding Mirror, & Shroud 

The scanner, folding mirror, & shroud shall be capabZe o4 with4tanding the environments listed in DR 1100, Table 111, (environmental 

criteria for external components) except as follows: 

1 1 

A. Shock - ao pen PIR No. 7223-MOL-278. 

8. Scannen. and Ford MihAVh - Envitonmentat AequiAements zhaLe. be 

reduced commemunate with the pAotection a.64onded by the 

4hAoud and iaiAing. 

C. Shroud - Enviunmentat kequiAement.A shalt. bereduced tommenzmate with the protection a44onded by the OiAin9. 

These components are externally mounted to the vehicle structure as defined 

onGE Drawing (later), and are located in zone 2 as defined in Figure 1 

of DR 1100. 

The free molecular heat load experienced by the protective shroud 

and other extended surfaces will be as shown in Figures 11, 12, 13, and 14. 

The temperature of the mounting surface for the GE furnished gyro 

assemblies shall be maintained within the limits of 0 to 100 degrees F. 

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3.1.2.4.2 Telescope 

The telescope shall be eapabte o4 w.alutanding the environments 

listed in DR 1100, Table 1, (environmental criteria for internal components) 

except that Ahock shaet be in. accordance with PIR No. 7223-MOL-278. The 

telescope is internally mounted in zone 2, as defined in Figure 1 of DR 1100. 

Temperature envelope drawing GE 711-00120 defines all of the 

console surfaces visible to the telescope along with their predicted temperature - time behavior and spectrophotometric properties. 

3.1.2.4.3 Optical Window 

The optical window shall be capab'e with/standing the apptoptiate 

environments listed in Table I of DR 1100 on its internal interface and Table III 

of DR 1100 on its external interface, except that shock zhate be in accordance 

with PIR No. 7223-MOL-278. 

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3.1.2.5 Transportability 

Procedures and design for transportability shall be in accordance 

with SSD exhibit 63-3 for highway and rail transportation, and in accordance 

with MIL-A-8421 for air transportation. Vibration/shock sensors and associated 

recording devices shall be provided. 

The packaging shall be adequate to maintain the specified cleanliness conditions of the component under the shipping environments specified. 

Containers shall bear precautionary labels or markings that are compatible 

with the specified cleanliness requirements. 

3.1.2.6 Human Engineering Considerations 

3.1.2.6.1 Field Flatness 

A design goal for the optical assembly is a flat image plane 

providing maximum resolution with minimal accommodation demands. 

3.1.2.6.2 Exit Pupil and Eye Relief 

It shall be a design goal that the exit pupil diameter and eye 

relief shall not result in overly restrictive head and eye positioning 

which could cause fatigue during prolonged optical assembly operations as 

described in section 6 of this specification. 

The size of the exit pupil and the amount of eye relief should 

allow full utilization of the total apparent 60 degrees field of view of 

the optical assembly, including the peripheral displays, with a minimum 

amount of head movement; vignetting and a loss of imagery resulting from 

head and eye movement during target search and activity evaluation should 

be minimized. 

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3.1.2.6.3 Controls & Displays 

Controls required for adjustments or normal operation shall 

be designed for operator convenience. The telescope mounted manual controls 

shall be designed for use in ambient light levels as low as 0.1 foot candle. 

All equipment shall be designed to permit normal control operation while 

the astronauts are in a space suit w.i,th gloved handS. All controls shall 

also be clearly visible at higher ambient light levels up to 30 foot candles. 

Paragraphs 3.5.4, 3.6.3, & 5, and 3.8 of MIL-H-27894 shall apply to this 

design. Technical order WADC-TR52-321 shall govern where applicable. 

MIL-STD-803 shall also be used as a guide. 

3.1.2.7 Safety 

The optical assembly shall be designed to conform to the 

requirements of -()- GE specification No. DR 1100. MIL-S-38130 shatt be 

used as a guide. 

3.1.2.7.1 Flight Safety 

Parts which may work loose in service shall be safety wired 

and/or shall have approved locking means applied. Finishes, lubricants, or 

other materials used in the component shall be carefully selected to avoid 

adding toxic fumes to a closed, recycling, atmosphere during an operating 

period of 30 days. Only materials on the approved materials list DR 1115 

or otherwise approved by General Electric shall be used. 

3.1.2.7.2 Ground safety 

All recognized class III and IV hazards, and potential hazards, 

as defined in MIL-S-38130A shall be reported to the General Electric 

Company by means of the prescribed hazard report. The optical assembly 

shall be designed to avoid creating a safety hazard to flight crews inside 

the vehicle or to the ground crews near the vehicle during ground checkout. 

3.1.2.7.3 Personnel Safety 

Design of components shall give prime consideration to the 

minimization of hazard to personnel in using or maintaining the equipment. 

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3.1.2.7.4 Explosive and/or Ordnance Safety 

Emphasis shall be placed on minimization of EMI hazards 

defined in DP1690 and upon interface specifications on grounding, shielding, 

and electrical supplies. 

3.2 Component Definition 

3.2.1 Interface Requirements 

3.2.1.1 Schematic Arrangement 

The following electrical interfaces shall be provided in accordance 

with Drawing No. later 

3.2.1.1.1 Scanner Electrical Interface 

A. A power interface between the acquisition subsystem and the 

torquers on the scanner gimbals. 

B. A power interface between the encoders and other sensors on the 

scanner and the GE-AVE electrical power and signal distribution 

subsystem. 

C. A signal interface between the encoders on the scanner gimbals 

and the acquisition subsystem. 

D. A power interface between the heater control unit -if requiredand the GE-AVE electrical power and signal distribution sub- 

__ system. 

E. A signal interface between scanner-mounted instrumentation 

and the GE-AVE command and instrumentation subsystem. 

F. A power interface between any pyrotechnic devices -if requiredand the GE-AVE. 

G. A power and signal interface between the gyro electronics 

and the acquisition subsystem. 

3.2.1.1.2 Telescope Electrical Interface 

A. A power interface between the derotation drive motor and 

the acquisition subsystem. 

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B. A power interface between the zoom drive motor and the 

acquisition subsystem. 

C. Power interfaces between the zoom and derotation position 

sensors and the GE -AVE electrical power and signal distribution 

subsystem. 

D. A signal interface between the zoom position sensors and 

the acquisition subsystem. 

E. A signal interface between the derotation position sensor 

and the acquisition subsystem. 

F. A power interface between magnification step drive motor 

and the acquisition subsystem. 

G. A power interface between the blanking mechanism drive and 

the acquisition subsystem. 

H. A signal and power interface between the sun sensor and the 

acquisition subsystem. 

I. A power interface between the peripheral display and the 

CC & I subsystem. 

3.2.1.1.3 Shroud Electrical Interface 

A power and signal interface between the shroud door drive motor 

and the acquisition subsystem. 

3.2.1.2 Mechanical Interface Definition 

3.2.1.2.1 Scanner Mechanical Interfaces 

The scanner shall have the following mechanical interfaces as 

defined on Drawing 

A. A harness terminated in two electrical connectors -per 

MIL-C-26482- to carry the electrical signals and power 

between the gimbals and the two penetration connectors in 

the lab module structure. 

B. A structural interface between the scanner mounts and the 

lab module structure. 

C. A mechanical interface to provide precise locations for 

ground alignment. 

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D. Mechanical interfaces with GE furnished gyro assemblies and 

associated harnesses. 

3.2.1.2.2 Telescope Mechanical Interface 

The telescope shall have the following mechanical interfaces 

as defined in Drawing -later-. 

A. Two hard mounted connectors-per MIL-C-26482- within 

the console to carry electrical signals between the 

telescope and the acquisition subsystem. 

B. A structural interface between the lab module structure and 

the objective end of telescope barrel. 

C. A structural interface between the lab module structure and 

the elbow section of the telescope barrel. 

D. Envelope dimensions and space allocations per GE Drawing 

No. -later-. 

E. A nonstructural interface between the cue projector and 

its telescope. 

3.2.1.2.3 Window Mechanical Interface 

The window dimensions, methods of mounting, finishes at 

mounting points, and load bearing requirements shall be as defined on 

Drawing No. -utter-. 

3.2.1.2.4 Shroud Mechanical Interface 

The shroud shall have the following mechanical interfaces as 

defined in Drawing No. -later- . 

A. A structural interface with the lab module. 

B. An envelope dimension and space allocation within the 

acrodynamic fairing per GE Drawing No. -later-. 

3.2.2 Component Identification 

3.2.2.1 Government Furnished Property List - none 

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3.2.2.2 Contractor Furnished Property List 

A. Gyroscopes -1 per gimbalB. Gyro Electronics and Interconnecting Cable 

3.2.2.3 Special Approval Components 

The following components require specification review. Backup analysis 

sufficient to justify selection of critical performance characteristics 

shall be provided. Contractor approval is required before procurement. 

A. 18 bit incremental shaft encoder 

B. 20 bit incremental shaft encoder 

C. Roll torque motor 

D. Pitch torque motor 

E. Derotation-( )-motor 

F. Power changer-( )- motor 

G. Zoom mechanism -( )-motor 

H. Limit switch for gimbals 

I. Roll bearings 

J. Pitch bearings 

K. Shroud drive 

3.2.2.4 Logistics Critical Component List -none3.3 Design and Construction 

3.3.1 General Design Features 

Each optical assembly consists of a scanner, folding mirror, and optical 

window, telescope, and shroud. The two-gimbal scanner is externally mounted 

to the laboratory module through its tracking pedestal. The folding mirror 

is separately mounted to the lab module structure. The optical window will be 

mounted by the lab module contractor into the lab module structure. The 

internally mounted telescope includes all the optical elements from the objective 

lens through the monocular eyepiece. The telescope incorporates derotation, 

magnification step change, and zoom mechanisms. It also includes means 

for manual focus adjustment and spectral and neutral density filters. 

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The telescope design makes provision for the insertion of externally provided 

image cue projection for display through the eyepiece. A device for switching 

the display from the scanner provided image to the cue projection image is 

included in the telescope. This device or another will provide for blanking 

of the target image upon receipp of a command signal. Thermal doors and 

associated drives, are provided in the shroud assembly. 

3.3.1.1 Weight 

Each optical assembly shall weigh no more than TBD lbs. 

3.3.1.2 Power 

The peak power required by each optical assembly shall not exceed TBD 

watts. -0- 

The average power required by each scanner during the tracking mode 

shall not exceed TBD watts. 

3.3.2 Selection of Specifications and Standards 

The order of precedence for the selection of specifications and 

standards shall be in accordance with MIL-STD-143. Only those military 

doucments listed in ANA bulletin 400 and/or DOD index of specifications and 

standards shall be interpreted as being group 1 documents as defined in MILSTD-143. The use of standards and specifications other than those listed or 

referred to by those listed in Section 2, herein, shall require prior approval 

of GE. Any MIL-STD-143 group III documents selected for use shall automatically 

necessitate the preparation of a specification control drawing which shall 

be so drafted as to establish the specific document being referenced, its date 

of issue, and control responsibility for its use. 

3.3.3 Materials, Parts, and Processes 

Microelectronic elements shall be used in electronics circuitry wherever 

their usage is reasonable for the particular application. In those instances 

where it can be shown to GE's satisfaction that the use of microelectronic 

circuits is not feasible, then discrete parts shall be used. These elements 

and/or parts shall be in accordance with GE specification No. DR 1110, (selected 

parts list). In the event they do not appear in the listing of DR 1110, data 

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shall be furnished in accordance with requirements of DR 1110 for their subsequent inclusion. 

Where discrete parts are used, modular packaging of these parts shall 

be used wherever possible. The modular packaging techniques to be employed 

shall be similar to those described in GE specifications S-30000, S-30001, and 

S-30002. 

Other materials, parts, and processes shall be in accordance with 

GE specification No. DR 1100,-()- DR 1112, DR 1113, and DR 1115. In the event 

these specifications do not suffice, nonconflicting portions of MIL-E-25366 and 

MIL-E-5400, may be used, subject to GE's approval. 

In the case of the use of equipment built to a design previously accepted 

by the government, it will not be necessary to change the design to use only 

parts that are on the MOL selected parts list provided that 

A. Evidence of prior acceptance of the equipment is submitted. 

B. Prior application-s- included demonstrated capability in 

equivalent or more severe environments than specified in paragraph 3.1.2.4 herein. 

C. The design is approved by General Electric. 

3.3.4 Standard and Commercial Parts 

For other than electronic or electrical parts maximum use be made of 

commercially available standard MIL, AN and MS parts. If it becomes necessary 

to use commercial parts other than those listed as standard, a list shall be 

submitted to GE identifying each part by name, catalog number, number of parts 

required, manufacturer's name and equivalent approved government specification 

-if available- which can be substituted for the commercial part. The reason 

and substantiation for the use of the commercial or nonstandard item shall 

also be submitted. 

3.3.5 Moisture and Fungus Resistance 

This component shall conform to the requirements of MIL-STD-454, 

requirement 4. Protective coatings will not be acceptable as moisture 

and fungus preventatives on parts which will lose the coatings during 

the normal course of manufacture, assembly, and test. Metallic materials 

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shall resist the detrimental effects of moisture, either by nature of the 

material, or by means of a process or coating similar to those specified 

in MIL-S-5002. Cadmium plating shall not be used. 

3.3.6 Corrosion of Metal Parts 

3.3.6.1 Electrolytic Corrosion 

Use of dissimilar metals in direct contact with each other shall be 

avoided as per the requirements of MIL-STD-454, requirement 16 and MS 33586 

unless suitably protected by plating, painting or other surface treatment in 

accordance with the requirements specified in paragraphs 3.2.6.1 and 3.2.6.3 

of GE specification No. DR 1100. 

3.3.6.2 Stress Corrosion 

Metals, techniques, and processes shall be selected and employed 

with regard to heat treatment procedures, corrosion protection, finish, 

assembly and installation, so that sustained or residual surface tensile 

stresses, stress concentrations and the hazards of stress corrosion, cracking 

and hydrogen embrittlement are minimized. 

3.3.6.3 Protective Treatment 

Protective treatment shall be accordance with MIL-F-7179- except 

paragraph 3.1.2, and GE specification No. DR 1100, paragraph 3.2-6.3. 

3.3.7 Interchangeability and Replaceability 

One optical assembly will be mounted on each side of the lab module. 

The left and right-hand optical assemblies shall be as near to mirror images 

of one another as feasible. There shall be a minimum of ocmponents which 

cannot be used in both installations. Interchangeability of optical assembly 

components between left and right installations shall be maximized. 

Each part, subassembly, or assembly bearing a particular supplier/s 

part number shall be completely interchangeable with all other parts, subassemblies, or assemblies bearing the same number. 

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The requirements of MIL-STD-454, requirement 7, shall apply. 

3.3.8 Workmanship 

This component, including all parts and assemblies, shall be constructed 

and finished in accordance with MIL-STD-454, requirement 9. Soldering, wiring, 

impregnation of coils, mating of parts, plating, riveting, machine screw 

assemblage, welding, brazing, and freedom of burrs shall also comply with 

MIL-STD-454, GE specifications S-30029, and S-30042 or they shall be in accordance 

with techniques employed by the supplier, all subject to prior approval by 

General Electric. Installation of wiring shall be in accordance with specification MIL-W-8160. 

3.3.9 Electromagnetic Interference 

This optical assembly shall conform to the requirements of paragraph 

3.2.11 of GE specification No. DR 1100. 

3.3.10 Identification and Marking 

Identification and Marking shall be in accordance with MIL-E-5400 

paragraph 3.1.1.9, MIL-STD-130, and MIL-STD-195. Selected colors shall be in 

accordance with FED-STD-595 and MIL-STD-795. 

3.3.11 Storage 

This optical assembly shall be capable of performance per paragraph 

3.1 after two years storage in an environment as defined in paragraph 3.1.2.4. 

3.3.12 Cleanliness 

This component shall be assembled in a clean area which meets the 

requirements of FED-STD-209, class 10,000, or shall be capable of being cleaned 

for use in such an area. 

3.3.13 Allowable Acoustic Noise. 

The sound pressure level output of the telescope shall be limited to that 

specified in General Electric specification DR 1100, paragraph 3.2.13. Appropriate 

noise control measures shall be developed to assure compliance with the requirements 

of DR 1100 for components whose inherent design is subject to the generation of noise. 

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4.0 Quality Assurance Provision4 

4.1 Engineering Test and Evaluation. This component shall be subjected to 

such tests as are necessary to provide data, not obtainabte by °ther testing speciiied hekein, to verify conformance with the requirements of Section 3. 

4.2 Fonmae Quatiiication Tests 

4.2.1 Analyses Belioke Testing 

These analyses shall include, but not limited to, review of engineering 

documentation, subcontractor internal documentation, historical and analytical 

summaries, and stress analyses performed. The following requirements of 

Section 3 shall be verified by review of analytical data prior to the start 

of environmental testing: 

A. MaintainabiLity (3.1.2.2) 

B. Human Factou (3.1.2.6) 

C. Satiety (3.1.2.7). 

D. Interface Requirements (3.2.1) 

E. Selection of Specifications and Standards (3.3.2) 

F. Matekiats, Notts, and Processes (3.3.3) 

G. Standard and CommeAciat Parts (3.3.4) 

H. Moisture and Fungus Resistance (3.3.5) 

I. Corrosion of Metal Parts (3.3.6) 

J. IntekehangeaWity and Reptaceabitity (3.3.7) 

K. Wonkman6hip (3.3.8) 

L. Identqication and Man/zing (3.3.10) 

M. Storage (3.3.11) 

N. Cteantine44 (3.3.12) 

4.2.2 Test Condition6 and Procedures 

Tut cohd.itiono and ptoceduAes skate conpAm to the tequitement4 off( 

GE oeeilcitati.ion No. DR 1100, pauguph4 3.3 tests and 4.2 test conditions. 

4.2.3 PeitioAmance yeAiliication Tests 

4.2.3.1 Dielectric Strength and Insulation Resistance Tests 

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Page 32 

The component shall be tested for dielectric strength and insulation 

resistance per paragraph 4.3.1.2 of GE specification No. DR 1100. If 

componantS employing transistorized circuits are of such a nature that they 

will not withstand this test, the manufacturer shall perform a test for 

dielectric strength and insulation resistance using the maximum voltages 

possible. These tests are subject to the approval of the General Electric 

Company. 

4.2.3.2 Corona and Arcing Test 

Corona and Arcing test per paragraph 4.3.1.1 of GE specification 

No. DR 1100. 

4.2.3.4 Scanner. Structural Dynamics 

The Stequency tesponse chatactekistics oS the gyAo output signeal 

wilt be measurted in ander to .insure that the tequitements o6 paitagtaph 3.1.1.1.8 

oS this zpeciSication ate met. 

4.2.3.5 Acceptance Tut and Opetabieity DemonstAation 

The component skate be 'subjected to a complete acceptance tut in 

accordance with Pant 11 oS this speci4cati.on. Success6a completion oi 

these tests is a pnetequisite Sot start o6 the 'subsequent tuts. 

4.2.4 QuatiSication Envitonmentat Test 

QuatiSication envixonmetat tuts shall be petytmed on two (2) 

components in accordance with pa/tag/mph 4.4 oS DR 1100 as noted in this 

speci6ication. 

4.2.4.1 Intetnae Components 

The Sottowing quatiSication test sequence shalt be petSotmed on 

the intetnae components: 

4.2.4.1.1 Accetemtion: The component Acta be placed £n the acceenation 

apparatus and given an accetetation oi 10 g's Sot 5 minutes along the 

vehicte x axis and an acceteAation o6 5 g's Sot 5 minutes along each oS the 

other tuy vehicte axes Son a total oS six ditections. The component shad 

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be nonopetating and in a Launch condition duting thiz test. 

4.2.4.1.2 Peir.iomnance Tut 

The 4ottowing items shall be checked: 

A. Opticat Magniiication and FLeLd o4 View (3.1.1.1.1) 

B. Rezotution (3.1.1.1.1.2) 

C. Image Rotation Capabitity (3.1.1.1.1.11) 

D. Cue Insertion and Stew StanUmg Ptovizion (3.1.1.1.12) 

E. Zoom and Magni4ication Change (3.1.1.1.21) 

F. Eye Retie4 (3.1.1.1.16) 

G. Petiphetat Dizptay (3.1.1.1.22) 

H. Manual Ovevti4e/1 (3.1.1.2.4) 

4.2.4.1.3 Vibtation pet DR 1100 paAagtaph 4.4.3.5 sot ptezzuAized campattment, zone 2, watt-mounted, Figune 10. The component shat be nonopetating during th,Lo test, and in a Launch condition. 

4.2.4.1.4 Pet4otmance Test 

Same as panagnaph 4.2.4.1.2 

4.2.4.1.5 Design Shock 

The component shall be subjected to tests which zimutate the 

anticipated shock zpectta (Figure 2 PIR No. 7223 MOL 278) induced by stage 

zepaitation on. other pyto-technic devicez. 

4.2.4.1.5.2 Pet4otmance Test 

Same as paragraph 4.2.4.1.2 

4.2.4.1.5.3 Ttanzpottation Shock 

The packaged component (ot an equivalent packaged inzttumented 

dummy) shaft be tested son itz ability to istatain ttanzpottation shockz in 

accotdance with Ptocedute III o4 MIL-STD-810 az mod. ied by Tabte IV in GE 

zpeci4ication No. DR 1100. 

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4.2.4.1.6 PetlioAmance Teat 

Same as patagAaph 4.2.4.1.2, actual component -L4 u4ed in .the 

ttanzpoAtation zhock teat. (not nequ4:Aed otheAmize) 

4.2.4.1.7 Acourtic no-Lee pet DR 1100 patagAaph 4.4.3.7. 

4.2.4.1.8 Peklimmance Teat 

Same as patagAaph 4.2.4.1.2. 

4:2.4.1.9 Tempetatute cyeUng pet DR 1100 patagtaph 4.4.3.1 except that 

the component zhatt be nonopenating du/ Ling thiz teat and petiOtmance teztz 

zhatt not be conducted. 

4.2.4.1.10 PeqoAmance Teat 

Same as panagtaph 4.2.4.1.2. 

4.2.4.1.11 TheAmat attitude pet DR 1100 pa/tag/mph 4.4.3.2 except opticat 

pettionmance zhatt not be meazuted. 

4.2.4.1.12 PeklioAmance Test 

Same as patagtaph 4.2.4.1.2. 

4.2.4.1.13 Oxygen compat-ibieLty pet DR 1100 paAagAaph 4.4.3.15. 

4.2.4.1.14 HeLican compatibie-ity pet DR 1100 patagtaph 4.4.3.15. 

4.2.4.1.15 Pet4otmance Teat 

Same as pcoagtaph 4.2.4.1.2 

4.2.4.1.16 EtectAomagnetic compatibility pet DR 1100 pa/Lag/mph 4.4.3.12. 

4.2.4.1.17 Leakage and Pneazuh.e IntegAity 

The component shatt be tested to demonztAate the teakage requitement 

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Page 35 

o4 patagnaph 3.1.1.1.25 and the ptessute integ4ity 4equixement4 06 paragraphs 

3.1.1.1.25 with a satiety 4actot o4 1.5. 

4.2.4.1.18 Endurance pet DR 1100 patagAaph 4.4.3.19. The component shaft 

be operated bon a putiod o 980 hours 04 the tote numben oi cyctes 

stated in pataglaph 3.1.2.3F o4 this 4peci4ication. This test shall be 

conducted in the ambient conditions teietenced in paAagtaph 4.2 o6 DR 1100. 

Duting this test, -the component shate demonstAate its ability to meet the 

4unctiona chanacteAistics speciged in patapaph 4.2.4.1.2 qte4 every 

100 houxs oti ope4ation,and be6o4e and Wen enduAance test. 

4.2.4.2 Exte4nat Components 

4.2.4.2.1 AcceteAation: 

The component shaft be placed in the accaenation apparatus and 

given an acceteta-tion oti 10 g's 04 5 minutes along the vehicee x axis and 

an acceeetation o4 5 g's bon 5 minutes along each o6 the others tub vehicte 

axes hors a totae oi six ditections. The component shaft be nonopetating 

dutirtg this test and shatt be in the Launch (stowed) condition. 

4.2.4.2.2 Pet4oAmance Test 

The Ottowi.ng items shael be checked: 

A. Scan Fieed (3.1.1.1.3) 

8. Scanner Onientation 3.1.1.1.4) 

C. &Armen. Gimba Acceteution (3.1.1.1.5) 

D. Scanners Gimbme Tongues (3.1.1.1.6) 

E. Scanner Gimbat Pozition Readout (3.1.1.1.9) 

F. Shroud Drive (3.1.1.1.24) 

G. Scannet Gimbal Dnive (3.1.1.2.5) 

H. Scanner G.imbaL. Encode46 (3.1.1.2.6) 

1. Sun Sensors (3.1.1.1.23) 

4.2.4.2.3 Vibration pet DR 1100 paragraph 4.4.3.5 bon pressurized compartment, 

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zone 2, watt mounted FiguAe 10. The component shate be nonopeAating 

duAing thiz -teat, and skate be in the Launch (ztowed) cond,ition. 

4.2.4.2.4 Pet6oAmance Tett 

Same as paAagtaph 4.2.4.2.2. 

4.2.4.2.5 Shock. Teztz 

Same as paAagAaph 4.2.4.1.5. 

4.2.4.2.6 PetlioAmance Teat 

Same as palLagtaph 4.2.4.2.2. 

4.2.4.2.7 Acourtic Noize 

Pen DR 1100 paAagtaph 4.4.3.7. 

4.2.4.2.8 Pet6oAmance Teat 

Same az panagAaph 4.2.4.2.2. 

4.2.4.2.9 Thetmat/Vacuum 

Pen DR 1100 panagAaph 4.4.3.3 except opticat peqoAmance zhate 

not be meazuAed. 

4.2.4.2.10 PenlioAmance Teat 

Same as pa)ulgAaph 4.2.4.2.2. 

4.2.4.2.11 EeectAomagnetic Compatibility pen DR 1100 patagAaph 4.4.3.12. 

4.2.4.2.12 EnduAance pet DR 1100 paAagnaph 4.4.3.19. The camponent zhatt 

be operated on. a pekiod ob 980 hours bon the total numbet o6 mechanizm 

cyceez stated in paragraph 3.1.2.3F oi thiz zpeci6ication. ThL teat shatt 

be conducted in the ambient conditionz reietcneed in pa/tag/mph 4.2 ob DR 1100. 

Doming the test the component shat demonztAate itz ability to meet the iunct.ional—

chavactenizticz, zpeciiied in paAagAaph 4.2.4.2.2 aktet event' 100 hours oi 

opetation. 

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4.3 Reliability Test and Analysis 

A reliability mathematical model of the optical assembly will be 

constructed showing the functional relationship of all parts and assemblies. 

A listing of all functional parts shall be supplied with a statement of applied operation stress levels for each part (voltage, current, mechanical 

loads, vibration, temperature, etc.) . For each part application, a failure 

rate shall be stated. Military Handbook MIL-HDBK-217 for electrical and 

electronic parts and SP 63-470, Vol. 1 (Farada) for all other parts shall 

be used as the controlling sources of failure rate data (with the use of 

appropriate application factors) unless use of other rates is justified 

by data derived from tests or prior proven experience in equivalent applications. Using the procedure above, the reliability and/or the MTBF for 

the equipment shall be computed and submitted to General Electric. This 

analysis, subject to approval by General Electric, will constitute adequate 

demonstration of the design reliability, provided that the computed reliability 

and/or the MTBF meets or exceeds the design requirement stated in paragraph 

3.1.2.1, and provided that the reliability model and associated reliability 

computation are updated for every subsequent change in configuration or 

application. 

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6.0 Notes 

General Optical Assembly Mission Operations 

During a payload pass one of the primary tasks of the crew will be to 

examine a series of targets in the optical assembly to determine the amount 

of military-relevant activity in the target area. The crewman will perform 

activity evaluation to provide data for priority determination to assist in 

the selection of target areas to be photographed by the main optics. Data 

from the correction of target L.O.S. and rate errors in the optical assembly 

may be used for computer updating for main optics photography. 

In the nominal operation mode, the initial optical assembly pointing 

commands will be provided by the on-board computer. In addition, the optical 

assembly system will be capable of operating in a limited search mode during 

which the crewmen can reposition the optical assembly L.O.S. to evaluate 

targets of interest in the near vicinity of the pre-programmed target. 

The basic events occurring during a target pass are: 

Acquisition scope slew to target 

Observe general weather/cloud cover conditions in target area 

Perform target search, as required 

Identify/validate target 

Correct position and tracking rate error 

Increase magnification, as required 

Perform target activity/weather evaluation 

Perform target priority decision 

The amount of time available for performing target pass tasks varies 

as a function of target density. In high density areas, targets will be 

available at a maximum rate of one target per four seconds requiring rapid 

performance of the target detection, acquisition and activity evaluation 

tasks. 

A more detailed description of optical assembly mission tasks can be 

found in CDRL item #107 entitled, Crew and Time Line Analysis, Volume I -SSH 

DIN 3849-252-1, dated 15 March 1967-. 

The finite resolution requirements for the optical assembly have been 

derived from the type and characteristics of the activity indicators to be 

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evaluated during mission operations. Several other characteristics of the 

optical assembly such as image plane characteristics, resolution fall off, and 

image brightness must receive human engineering evaluation to optimize 

optical assembly design. 

Telescopes typically have different foci at various image axes resulting in curved image planes. In normal telescopes, the central optical axis 

of the telescope is used for viewing. However, positioning accuracy of 

the optical assembly results in a distribution of targets of interest across 

the entire field of view of the telescope, thus, requiring the crew man to 

scan the entire field of view and to detect targets at different loci in the 

field of view. A curved image plane or differences in the tangential and 

saggital foci of the optical assembly image requiring visual system accommodation by the crew man are undesirable since they would result in altered search 

patterns, crewman fatigue and/or increased time requirements for searching and 

detecting targets. 

During target acquisition operations, the crew member will shift his attention between cue materials, the optical assembly and the main optics. The 

size of the exit pupil and eye relief of the optical assembly system must be 

sufficient to insure rapid acquisition of the optical assembly image following 

changes in head and eye position during shifts between the cue, optical assembly, 

and main optics displays. 

10.0 Appendix 

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(Use right-hand rule for positive rotations) 

Figure 1. Orbiting Vehicle Coordinates 

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Page 45 

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-SEW- SPECIAL HANDLING 
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Page 46 A 

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APPROVED FOR 

EASE 1 JULY 2015 

Addendum 1.2-B 

1.0 Scope Human Engineering Specification 

1.1 This specification establishes the human engineering requirements for the 

Acquisition Optics (AO) which is a component of the Acquisition and Tracking 

System (ATS). 

2.0 Applicable Documents 

2.1 The following documents, of exact issue shown, form a part of this specification 

to the extent specified herein. 

AFSCM 80-3 Handbook of Instructions for Aerospace 15 July 1966 

Personnel Subsystem Design 

MIL-HDBK-141 Optical Design 5 October 1961 

EC-331 AO Subsystem Performance/Design and 23 December 1966 

Qualification Requirements 

DIN 3694-200-1 Acquisition Optics Work Statement 3 January 1967 

WS 011 B 

3.0 Requirements and Applicability 

3.1 General 

The principles, procedures and criteria of human engineering shall be applied, 

to the areas specified in 3.1.2, to ensure that adequate consideration is given 

to the capabilities and limitations of man as a component of the ATS. Within the 

parameters established by the AO Performance/Design Specification and the AO Work 

Statement, a human engineering effort will be provided to increase and preserve the 

effectiveness of the human component during the operation and control of the ATS. 

The AO design will be adapted to the established capacity and ability of man to produce 

a more effective system. 

3.1.1 Human Engineering Effort 

The human engineering effort shall include active participation in the following 

major interrelated areas of system development. 

a. System analysis to identify, define and allocate system operation and control 

functions 

b. Selection, definition, and detail design of equipment associated with the 

system functions requiring human performance 

ltek ; ITEK CORPORATION 

L . 1 LEXINGTON, MASSACHUSETTS 02173 

RE 

NR 

TITIE 

AO HUMAN ENGINEERING SPECIFICATION 

CODE IDENT 

92208 

DOC. NO. 

114281 

V 

SHE ET 

RE 

CMG NO 

1101.2 10/66 

• 4re • 

PROJ NO. 9300 

4 SFEL;01. • • HANDLING .1-"KLF -7. -- 

SHEET 2 OF 6 
---NRO APPROVED F 11 

1 JULY 2015 RELEASE 'PECIAL HANDLING SECPEE 

c. Testing and evaluation to verify that the design of the equipment meets human 

engineering requirements and is compatible with the overall system requirements 

d. System reliability evaluation, safety engineering analysis, and design for 

maintainability. 

3.1.2 Areas of Application 

The detail design requirements of EC-331 and the imposed location of the eyepiece 

principally limit the Itek AO human engineering effort to the following: 

a. Design of manual backups and controls 

b. Human visual interface factors involved in the design of the optical system 

c. A limited study to determine human eyeball dynamic resolution for the mission 

parameters specified in EC-331 

d. A sustaining effort to anticipate and identify human engineering problems and 

advise G.E. accordingly. 

3.1.3 Guidance Documents 

3.1.3.1 Manual Backups and Controls 

The following sections of the indicated documents shall be used as a guide for the 

design of the manual backups and controls. 

a. Section 7 and 10 of MIL-STD-803 A-1 

b. Section 7 and 10 of MIL-STD-803 A-3 

c. Part B, Chapter 4 of AFSCM 80-3 

3.1.3.2 Human Vision 

The following sections of the indicated documents shall be used as a guide for 

optical design and performance evaluation for the AO human visual interface. 

a. Part A, Chapter 5 of AFSCM 80-3 

b. Section 4 and 15 of MIL-HDBK-141 

4.0 Program Implementation Plan 

4.1 Manual Backups and Controls 

4.1.1 Analysis 

Manual backups on AO mechanisms shall be analyzed to ensure efficient, reliable 

and safe human operation. For each required mechanism, design approaches will be 

analyzed and compared from a standpoint of: weight, power requirements, reliability, 

Itek LEXINGTON, MASSACHUSETTS 02173 

I TEK CORPORATION -,TLE 

AD HUMAN ENGINEERING SPECIFICATION 

CODE (DENT DOC. NO. 

92208 114281 

SHEE

REv

T 

CMG NO PROS NO. 9300 SHEET 3 oF6 

SPECInLHANOLING E104.2 10/66 
CODE IDENT DOC. NO. 

92208 

E 101,2 10/66 brkCIAL HANDL.11't 7ii-..C.;1(k. 

NRO APPPowFn FoR 

RELEASE 1 JULY 2015 SP CiAL HAND! iNr '• • " 

1, 

function performance and human engineering considerations. A failure mode analysis of 

each mechanism will be undertaken as part of this effort. One purpose of this analysis 

shall be to deterMine the beat trade-off between overall reliability, manual torque 

requirements, and the selection of where to couple the manual control to the drive 

train. 

4.1.2 Design Criteria 

In general, the manual control shall be descriminable both visually and tactually, 

possess good gripping characteristics, conform to standard of direction movement 

relationships and be functionally suitable. 

4.2 Human Visual Interface 

Investigations shall be undertaken to determine human visual interface problems 

and requirements. These shall be reviewed with C.E. to obtain direction, information 

and analysis that may be required. Within the parameters established by the system 

specification, the objective of this effort shall be to provide an optical system 

consistent with the capabilities and limitations of the user's eye. Performance in 

excess of that allowed by the AO exit pupil/eyeball combination shall not be required. 

4.3 Dynamic Resolution Test 

A limited test shall be conducted to determine the affects of image motion and the 

AO apparent field on the human eye performance for the parameters specified in EC-331. 

These parameters shall be simulated to a first order level. The results and recommendations from this investigation shall be furnished to C.E. to assist in: defining 

system performance, establishing image stabilization control requirements, substantiating 

the need for possible additional tests. 

4.4 Organization 

4.4.1 Design Implementation 

Detail design involving human engineering considerations shall be the responsibility 

of the project design engineering group and the project optical engineering group. 

4.4.2 Systems Engineering 

The project systems engineering group participation in the human engineering effort 

includes the following: 

-;ITLE 

t 

AO HUMAN ENGINEERING SPECIFICATION 

CH G NO 

ITEK CORPORATION Kik LEMPAGTON. MASSACHUSETTS 02173 

PROJ NO. 

114281 

SHEET 

REV 

9300 SHEET 4 OF 6 
NRO AofltetEtrfeR 

RELEASE 1 JULY 2015 ti Li, 

a. Provide requirements and guidance for the design of the manual backups and 

controls. In this endeavor assistance will be obtained from Itek staff 

specialists not directly assigned to the project. 

b. Maintain liaison with the design engineering group and optical group to ensure 

inclusion of human engineering criteria in the design process. 

c. Advise C.E. on human engineering problems and interfaces for the manual backups 

and controls. Included in this is the identification of required studies to 

resolve problems and the estimated effect on the system if the problem is not 

studied and resolved. 

4.4.3 Optical Design 

The project optical engineering grout, participation in the human engineering 

effort includes the following: 

a. Identify problems and establish requirements for the human visual interface. 

b. Apprise G.E. of visual interface problems. Included in this is the identification 

of required studies to resolve problems and the estimated effect on the system 

if the problem is not studied and resolved. 

4.5 Signature Approval of Drawings 

Overall layouts, detail design drawings and specifiCations for the manual controls 

and the eyepiece design shall be reviewed for human engineering considerations. The 

signature approval of these documents by design, systems and project management personnel 

shall verify that the configuration and arrangement of controls and the eyepiece 

design will satisfy the operator-instrument performance requirements. 

4.6 Project Design Reviews 

Part of project design reviews conducted by the project management and the staff 

design review team will include a review of the human engineering requirements of this 

document and how they are being met. 

5.0 Design Verification 

5.1 Mock-Ups 

The form and external dimensions of all manual controls shall be provided on 

deliverable mock-ups. 

TITLE 

ltpk I TEK CORPORATION 

LEXINGTON. MASSACHUSETTS 02173 

' 

' ' I 

AO HUMAN ENGINEERING SPECIFICATION 

CODE (DENT 

92208 

DOC. NO. 

114281 

SHEET 

REV 

(MG NO 

F 04,2 V", 

PROJ NO 9300 'SHEET 5 OF 6 

-1A I.) 1 —i 7 
_110.APPROVED FOR" - 

RELEASE 1 JULY 2015 SPEriN HA ..IDLING' SE.Cr;', -- T 

5.2 Special Deliverable Engineering Pieces 

Special engineering pieces of the mechanized components shall possess the required 

manual controls. 

5.3 Qualification Tests 

Manual controls will be tested for function as part of the qualification tests for 

the AO subsystem. Off-axis resolution of the instrument will also be determined as a 

check on the eyepiece performance in the off-axis region. 

TITLE ITEK CORPORATION 

Itek ' 

, LEXINGTON, MASSACHUSETTS 01173 

SHEET 

REv AO HUMAN ENGINEERING SPECIFICATION 

• 

CODE (DENT 

92208 

DOC. NO. 

114281 

SPECIAL I IANDLING 

CHG NO 

1. 104.2 10/66/.1111 

PROJ NO. 9300 ISHEET 6 OF 6 
- NRO APPROVED FOR 

RELEASE 1 JULY 2015 

-Sy 

SPECIAL HANRINGta-i- 7 Page 1 of 7 pages 

Addendum 1.2-C 

Safety Engineering Criteria 

1.0 Scope 

1.1 This specification establishes the safety engineering requirements for 

the Acquisition Optics (AO) which is a component of the Acquisition and 

Tracking System (ATS). 

2.0 Applicable Documents 

MIL-S-38130A System Safety Engineering of Systems and Associated 

Subsystems & Equipment; General Requirements For 6/6/66. 

MIL-W-8160D AM1 Wiring, Guided Missile, Installation of, General 

Specification for 12/24/63. 

MIL-E-5400 H Electronic Equipment, Aircraft, General Specification 

For 6/1/65. 

MIL-STD-195 Marking of Connections for Electronic Assemblies 

10/20/55. 

MIL-STD-2202C Test Methods for Electronic and Electrical Component 

Parts 9/12/65. 

EC 331 Performance/Design and Qualification Requirements 

Optical Assembly 12/29/66. 

IR110W, Design, Environmental Criteria and Test Requirements 

Specification for Components of MDL Mission Payload 

System Segment - March 1967. 

DR 1112 Selected Processes for Use in the Mission Module, 

General Specification for 4/18/66. 

DR 1115 Selected Materials for Use in the Laboratory Module 

November 1966. 

SPECIAL HANgLING/SEERET 
NKU Al-'1"KUVEU I-UK 

RELEASE 1 JULY 2015 

POI PPM!I" If"

- 

Page 2 of 7 pages 

DP 1690 Specification of EMC Requirements For 

Equipment and Subsystems MOL 11/11/66. 

Doc. No. 114281 AO Human Engineering Specification 6/6/67. 

Doc. No. 114218 EMC Design Criteria and Design Requirements 

4/12/67 

3.0 Requirements and Applicability 

3.1 General 

The principles, procedures, and criteria of safety engineering shall be 

applied to the design, development fabrication, test, installation, and 

checkout of the AO's to eliminate or reduce all equipment operational 

hazards. The critical nature of the mission requirements imposes a 

stringent safety requirement to safeguard flight and ground personnel 

and to avoid the financial impact and program delays resulting from 

accidents. 

Within the parameters established by the AO Performance/Design Specification and the AO Work Statement, a safety engineering program will be 

undertaken to ensure that: 

1. Maximum safety consistent with operational requirements has been 

designed into the system. 

2. Adequate controls over known hazards, inherent to the product, are 

established to protect personnel, equipment, and property. 

3. Minimum risk is involved in the acceptance and use of new materials. 

4. Hazards associated with the AO are identified, reported, and 

eliminated or controlled. 

5. The requirements for retrofit actions and the resultant cost to 

eliminate or control hazards are reduced. 

SPEW HANIIII411 /OMIT 
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3.2 Gross Hazard Evaluation 

The following gross hazard evaluation is based on the requirements of 

paragraph 3.4 of MIL-S-38130A. Accompanying each hazard is its applicability to the AO design and the means of hazard control or elimination. 

3.2.1 Isolation of energy sources. Electrical power requirements are low. 

Internal voltage requirements do not exceed 33V, external requirements 

do not exceed 18V. These energy sources will be controlled qnd isolated 

by: use of good design practices, use of processes in accordance with 

DR 1112, use of materials in accordance with DR 1115, installation of 

wiring in accordance with MIL-W-8160D AM1, workmanship in accordance 

with MIL-E-5400 paragraph 3.1.1.9,and MIL-STD-195, insulation resistance 

will be tested per paragraph 4.3.1.2 of DR 1100A. 

3.2.2 Fuels and Propellants. Fuel and propellant compatibility is not 

applicable to the AO since the externally mounted components are 

shielded by the shroud and fairing. 

3.2.3 System Environmental Constraints. The system shall be designed to meet 

the performance requirements of EC 331 and the environmental requirements of DR 1100A. The ability of the system to meet the environmental 

requirements, which includes cabin and vehicle compatibility, in a safe 

manner shall be demonstrated by the environmental tests of DR 1100A. 

3.2.4 Explosive devices and their hazard classification. There is a possibility 

that explosive devices will be used in the external AO assembly. If 

explosive devices are utilized, they will be analyzed and tested from 

the following standpoints: (1) Minimum charge to adequately perform 

function. (2) Reliable means of preventing accidental discharge. 

(3) Encasement to prevent fragmentation. (4) Ability of support structure 

and adjacent areas to withstand detonation. (5) The prevention of 

SPECIAL IMPtIrMirs' -NI 
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SPECiAl Pr7. 1 Page 4 of 7 pages 

inadvertent firing of explosive devices is covered by paragraph 3.2.7. 

3.2.5 Compatibility of materials. Materials shall be selected for use in 

accordance with DR 1115 so as to avoid flammable, odor, or toxic 

hazard. 

3.2.6 Human Factors. Manual controls and backups shall be designed and 

analyzed to meet the requirements of paragraphs 3.1, 3.1.3.1, 4.1.1, 

and 4.1.2 of Document 114281 to ensure safe reliable human operation. 

The optical assembly shall include a sun sensor and blanking mechanism 

to avoid sun viewing. A hazard report shall be 

submitted to G.E. to cover other possible forms of HI energy radiation 

that may constitute a safety problem. 

3.2.7 Effect of transient current and radio frequency energy. The ability 

of the system to safely withstand momentary overpotentials shall be 

demonstrated by meeting the requirements of paragraph 4.3.1.2 of 

DR 1100A. This paragraph requires the performance of the dielectric 

strength (Method 301) of MIL-STD-202 as an acceptance test. The proper 

gas atmosphere for the performance of this test shall be investigated 

Radio frequency energy shall be controlled and limited by meeting 

the requirements of DP 1690 and Document 114218. The prevention of 

inadvertent firing of pyro circuits is covered by paragraph 3.8.5 of 

Document 114218. The sun sensor shall meet the requirements of 

paragraph 3.1.1.1.23 of EC 331. The possibility of radio frequency 

blocking of'eun sensor actuatirm shall be investigated. If required 

necessary safeguards to prevent blocking shall be incorporated into the circuit and 

tested for effectiveness. Electrical components such as motors, switches, 

relays, etc. used in the equipment shall be hazard free. Particular 

attention shall be given to eliminating any sources or contributors to 

flammability. SPECIP. IPTni.lristmfor 
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Page 5 of 7 pages 

3.2.8 Pressures Beal backup. The pressure integrity of the telescope shall 

meet the requirements ofp aragraph 3.1.1.1.19 of EC 331. 

34.9 Structural Integrity. The structural integrity of the AO shall be 

demonstrated by meeting the acceptance and qualification tests of 

DR 1100A. 

3.2.10, Documentation and Training. Training programs associated instructional 

material, and other manuals shall include proper procedural action for 

safe operating, handling, maintenance, and installation of the A0. 

3.3 Safety Procedures and Controls 

3.3.1 Controls and checks shall be established so that inherent design safety 

is not inadvertently degraded by assembly errors, improper test procedures, inadequate maintenance practices, or careless handling during 

transportation. 

3.3.2 Training programs and instructional material will include coverage of 

proper procedural action for safe operating handling, maintenance, and 

installation of the A0. 

4.0 Program Implementation Plan 

4.1 Hazard Reports 

Itek shall prepare a hazard report per G.E.-MOL-S-128, for submission to 

G.E. whenever a hazard is recognized regarding the use or application 

of the A0. Hazard reports shall describe the hazard, alternative solutions, 

recommended solution and action planned to eliminate or reduce the hazard. 

Itek shall submit a report upon identification of each hazard or potential 

hazard and another report showing final disposition of the problem. The 

report showing final disposition shall describe action actually taken or 

problem solution such as safety devices, design improvements, warning 

devices, and special procedures. 
NRO APPROVED FOR 

----71706.1.41 

RELEASE 1 JULY 2015 

SPEW, Page 6 of 7 pages 

4.2 Safety Engineering Reviews 

Project design reviews and TD meetings will include a review of the 

safety engineering requirements of this document and how they are being 

met. 

4.3 Approximately two weeks prior to PDR a safety engineering conformance 

review shall be conducted. The purpose of this review shall be to 

ensure that the requirements of this document are being met. 

4.4 Signature Approval of Documents,Layouts, Assembly Drawings, Detail Design 

Drawings shall be reviewed for safety engineering consideration. The 

signature approval of these documents by design, systems, and project 

management personnel shall verify the design meets the requirements of 

this document. 

4.5 Quality Control Responsibility 

Part of the project Q.C. function shall be exercise of proper controls so 

that inherent design safety is not inadvertently degraded by assembly errors, 

improper test procedures or careless handling. 

4.6 Design Responsibility 

Detail design involving safety engineering considerations shall be the responsibility of the project design engineering group, the project reliability 

group, and the project optical engineering group. Prime responsibility 

for safety eingineering implementation resides with these groups. Safety 

evaluations are to be incorporated into the detail design process early 

enough in the design cycle so that possible changes can be accomplished 

easily and economically. Emphasis is to be placed on preventive design 

rather than after-the-fact corrective or supportive role. The safety evaluations performed should be systematic in nature, quantitative in character, 

compatible with other design trade-offs and system evaluation functions. 

SPECi At 11,41B! IMI.!Et 
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REL ASE 1 JULY 2015 Page 7 of 7 pages 

-Ns 

4.7 System Engineering Responsibility 

The project engineering group participation in the safety engineering 

effort includes the following: 

a) Maintain liaison with the design engineering group and the optical 

engineering group to ensure inclusion of safety engineering criteria in 

the design process. 

b) Identify and analyze AO hazardous failure modes and possible improper 

procedural action by operating personnel. 

c) Participate in any required trade-off studies where safety requirements 

are involved. 

d) Prepare and submit hazard reports as required by GE-MOL-S-128. 

4.8 Nonconforming Parts 

When for compelling reasons a nonconforming part is considered for acceptance under established MRB procedures, the part shall be rejected 

if the nonconformance in any way degrades inherent safety. 

SPECIAL HANDLIMSERII 
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Addendum 1.2-D 

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NROAPPROVEDFOR SPECIAL rktli ■i DUNG SCCR:, RELf4E 1 JULy 2015 INTEROFFICE MEMORANDUM 

AcUtntLyn 1,2 - E Date: 18 Sept. 67 

Page 1 of 2 Pages 

To: J. Boll Facility: Burl. #11 349-67-492 

From: H. Simmons Facility: Burl. #11 

-&flaject TEMPERATURE SENSORS FOR TELEMETRY 

In order to provide temperature monitoring of critical AO components, 

temperature sensors will be required for each telescope. Preliminary 

locations and quantities are listed below. The locations are subject to 

change pending further analysis. Also, if heater control units are necessary, additional temperature sensors will be required. 

The type of sensor desired is the bonded KP Series resistance thermometer made by RdF Corporation (or equivalent). The carrier material 

for the sensor grid is mica and the resistance wire is CP platinum. This 

resistance thermometer has a wide range (-300 to 10000F), high sensitivity, very good stability, very good repeatability, very good response, 

and a high signal output. Each sensor requires two lead wires capable of delivering approximately 2 to 10 MV to resistance varying between 50 and 200 ohms. 

One major reason for choosing this type of sensor is because they 

lend themselves to the printed circuit lead cable being considered on 

the scanner assembly. 

TEMPERATURE SENSOR LOCATION TYPE QTY, 

1. Outside, leading edge of Bonded Resistance I 

shroud Thermometer 

2. Inside on skin, leading 

edge of shroud. 

3. Inside insulation, leading 

edge of shroud 

4. Inside skin of shroud door 

5. Housing of scannet 

roll torque motor 

6. Housing of scanner 

pitch torque motor 

7. Housing of roll 

axis encoder 

8. Housing of pitch 

axis encoder 

9. On scan mirror bezel (one 

near gyro mounting pads) 

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TEMPERATURE SENSOR LOCATION TYPE QTY. 

10. 

11. 

12. 

13. 

14. 

15. 

16. 

17. 

18. 

19. 

20. 

On rear surface of scan 

mirror 

On exterior fixed fold 

mirror bezel 

On rear surface of fixed 

fold mirror 

Inside housing of shroud 

door drive motor 

On radiator skin in shroud 

area 

Zoom drive motor area 

Derotation drive motor area 

Inside telescope tube near 

objective elements 

Inner surface of telescope 

near peripheral display 

Inside telescope near 

Pechan prism 

On penetration fitting 

TOTAL sensors per 

rr 

Bonded Resistance 

Thermometer 

fl 

/V 

If 

If 

If 

2 

1 

1 

1 

1 

1 

1 

1 

1 

1 

telescope 22 

HS/ rrinun 

c. c. 

A. Aube 

J. Berenholz 

M. Berkowitz 

D. Bott 

D. Breslow 

P. Clifford 

R. Heath 

G. Lenertz 

E. Powers 

R. Rosenthal 

—1kt-AAy 1 

H. Simmons 

Dist. 

App'd 

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2.0 Compatibility of the AO with other equipment. 

2.1 Interface Status. The primary method of establishing and controlling 

interface compatibility is through the generation and subsequent revision of 

Interface Control Drawings (ICD). 

On Sept. 15, 1967 the Itek Project manager notified the GE subcontracts 

manager that in the absence of acceptable ICD's, the PDR report would be 

submitted on the basis that our present design is compatible with all interface requirements. Therefore, only a brief summary of interface status is 

given rather than the usual item by item compatibility determination. 

(see 9300-67-283) 

To improve the generation and formal documentation of interface 

information Itek has proposed a series of semi-monthly working group meetings. 

It was further suggested that detailed agenda be prepared for these meetings 

and that each meeting be confined to one or a small group of subjects in 

order to maximize the effectiveness of the participants. The meetings 

should commence immediately. (see 9300-67-272) 

2.2 Space Allocation Compatibility 

Preliminary ICD 711-03005 was reviewed on Sept. 13th by Itek and GE 

personnel. At this time Itek reiterated certain required changes. These 

changes consist principally of: 1) shroud door definition, 2) modifications 

in the window area, and 3) shear mount definition. Further effort is required 

to update this drawing to an acceptable level. 

2.3 Mechanical ICD 

Preliminary ICD 711-03038 was reviewed by Itek and GE personnel on 

Sept. 13. Further effort is required to update this drawing to an acceptable 

level. 

2.4 CFE ICD 

No preliminary ICD has been received. 

2.5 Electrical ICD 

On September 7, 1967 a preliminary copy of a rough draft of the electrical 

ICD was reviewed. This document, GE number DIN 50029-8Q-2, is being 

revised by G.E. to include: 

1) Identification of all required data 

2) Use of standard notations and symbols 

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3) Specification of required data 

4) Proper format 

No date has been set for completion of this ICD. 

2.6 Recommended ICD Items 

To fulfill the intent and purpose of the ICD the following items have 

been suggested to GE for inclusion in ICD's. 

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MECHANICAL ICD 

1.0 MOUNTING INTERFACE 

1.1 Scanner Assembly 

1.1.1 Vehicle coordinates of three mounting points 

1.1.2 Physical description of mating interface surfaces 

1.1.3 Tolerances of scanner mount point locations (vehicle 

coordinates) 

1.1.4 Flexibility influence coefficients 

1.1.5 Alignment adjustment required 

1.1.6 Thermal properties of mounting fittings 

1.1.7 Definition of fasteners and responsibility assignment 

1.1.8 Electrical bonding requirements 

1.1.9 Deflection limits of the three mounting points 

1.2 Fold Mirror Assembly 

1.2.1 Vehicle coordinates of three mounting points 

1.2.2 Physical description of mating interface surfaces 

1.2.3 Tolerances of three mount point locations (vehicle 

coordinates) 

1.2.4 Flexibility influence coefficients 

1.2.5 Alignment adjustment required • 

1.2.6 Thermal properties for mounts 

1.2.7 Definition of fasteners and responsibility assignment 

1.2.8 Electrical bonding requirements 

1.2.9 Deflection limits of three mounting points 

1.3 Window 

1.3.1 Location with respect to telescope objective end 

mounting interface 

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0 

1.3.2 Perpendicularity'and concentricity with respect to 

telescope optical axis 

1.3.4 Maximum wavefront deformation 

2.3.4.1 Unmounted 

2.3.4.2 Mounted 

1.3.5 Thickness, diameter and material 

1.4 Shroud 

1.4.1 Physical description of mating interface surfaces 

1.4.1.1 Size and shape including flatness 

1.4.1.2 Finish 

1.4.1.3 Material 

1.4.1.4 Thermal properties 

1.4.1.5 Deflection envelope with respect to pressure 

shell 

1.4.2 Description of interface fasteners 

1.4.2.1 Responsibility 

1.4.2.2 Location and tolerance on location 

1.4.2.3 Deflection limits with respect to each other 

1.4.2.4 Fastener loads 

1.4.. Electrical bonding requirements 

1:5 Tllescope 

1.5.1 Objective End 

1.5.1.1 Mounting location, shape, and dimensions 

1.5.1.2 Physical description of mating interface 

surfaces 

1.5.1.3 Tolerances on mounting 

2.-41 

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1.5.1.4 Bolt pattern definition, pattern, size, 

threads, etc. 

1.5,1.5 Flexibility Influence Coefficients 

1.5.21 Shear Mount 

1.5.2.1 Mounting Pad Location, shape and dimensions 

1.5.2.2 Physical description of mating interface 

surfaces 

1.5.2.3 Tolerances on mounting pad 

1.5.2.4 Tolerances with respect to objective end mount 

1.5.2.5 Mount definition - bolt size, clearance, 

threads, etc. 

1.5.2.6 Flexibility Influence coefficients 

1.5.2.7 Alignment provisions 

2.0 MASS PROPERTIES 

2:1 SCanner Assembly 

' 2.1.1 Weight 

' 2.1.2 C.G. 

2.2 Fold Mirror Assembly 

2.2.1' Weight 

212.2 C.C. 

me • Window Weight 

2.4 Shroud 

2.4.1 Weight 

2.4.2 C.G. 

2.5 Gimbal Pitch and roll inertias 

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2.6 Telescope 

2.6.1 Weight 

2.6.2 C.G. 

2.6.3 Moments of inertia 

3.0 CABLING AND CONNECTORS 

3.1 Penetration connectors 

3.1.1 Location 

3.1.2. Shell Size 

, ,3.1.3 ,Orientation 

3.1.4 •Mating capability 

3.2 E.?cternal Cable Harness 

3.2.1 Routing on radiator 

3.2.2 Fasteners to radiator 

3.3 Telescope connectors 

3.3.1 Type of Connectors 

3.3.2 Location of Connectors 

3.3.3 Orientation of Connectors 

, s 

3.3.4 Mating Capability 

4.0 MANUAL BACKUP DEFINITION 

t. 

4.1 Changer Mechanism 

4.1.1 Configuration 

4.1.2 Location 

4.1.3 Motion and Forces required 

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4.2 Blanking Mechanism 

4.2.1 Configuration 

4.2.2 Location 

4.2.3 Motion and Force Required 

4.3 Rotation Mechanism 

4.3.1 Configuration 

4.3.2 Location 

4.3.3 Motion and Force Required 

4.4 . Zoom Mechanism 

4.4.1, Configuration 

,4.4.2 .Location 

4.4.3 Motion and Force Required 

5.0 GIMBAL. ALIGNMENT 

5.1 Definition of alignment references per paragraph 3.1.1.2.1 

of EC331B 

5.2 Encoder 

6.0 INTERFACE WITH CUE PROJECTOR 

6.1 ' Required opening in elbow structure 

6.2 Alignment of cue mirror to cue projector 

6.3- *4Optical parameters of projected image 

7.0 THERMAL 

lorke• External temperature history of the 

to the radiator beneath the shroud 

7.2 Internal temperature history of the 

through powered flight 

7.3 Penetration Fitting 

thermal insulation mounted 

fairing from pre-launch 

7.3.1 Window Temperature Control Requirements 

railvuLli\i■J Zt464- 

— 7 

, At 

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t LANUL,r,:(3 

7.3.2 Fold Mirror Temtif$ratures Control Requirements 

7.3.3 Penetration Fitting Heater definition 

7.4 Thermal Map of Bays 2 & 8 

7.5 Thermal Map of Bays 3 & 7 

7.6 Temperature history of penetration fitting around telescope 

objective end. 

8.0 CLEANLINESS AND SEALING REQUIREMENTS 

8.1 The fairing shall prevent contamination or degradation of 

the protective shroud thermal control surfaces. 

8.2 All penetrations of the radiator beneath the shroud shall be 

sealed by the vehicle contractor to prevent contamination of 

the AO external hardware. 

U.,1 AL A "difr64419F 

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LL,u1L nmivuLING 

SPACE ALLOCATION ICD 

1.0 EXTERNAL SPACE ENVELOPE 

1.1 Radiator configuration 

1.1.1 Bead pattern reference to vehicle coordinates 

1.1.2 Bead pattern elimination for scanner clearance 

1.1.3 Radiator and Ramp configuration at LM/MM interface 

• 

1.1.4 Shroud footprint to define surface blockage 

1.2 Launch Configuration 

1.2.1 Space allocation under aerodynamic fairing including 

allowances for radiator movements during ascent 

1.2.2 Space restrictions due to aerodynamic fairing separation 

. :devises 

1.2.3 Ascent Venting 

1.3 Stowed Configuration (On-orbit) 

1.3.1 Space allocation including allowances for radiator 

movements for mission duration. 

1.3.2 Restrictions due to proximity of other LM subsystems; 

e.g., fiewport, waste management port, horizon scanner. 

1.4 Operational configuration (on-orbit) 

1.4.1 Space allocation including allowances for radiator 

movements, door operation and scanner operation for 

any LOS position. 

1.4.2 Restrictions due to proximity of other LM subsystems 

such as the horizon scanner 

.t. • 1.4.3 Interferences with ATS line Of sight 

1.4.4 Sun Angle Restrictions 

2.0 INTERNAL SPACE ENVELOPE 

Referenced to vehicle axes radially and station numbers longitudinally 

2.1 Normal operational space envelope 

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2.2 Space Envelope for Manual Backup Operation 

2.3 Field Break Deiinition 

2.4 Panel Clearance 

..1 

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C.F.E. ICD 

1.0 MECHANICAL 

1.1 Gyro 

1.1.1 Outline drawing including connector location 

1.1.2 Weight, C.G. and inertias 

1.1.3 Mounting points and tolerances 

1.1.4 Physical description of mounting interface 

1.1.5 Input axis to output signal trAnsfer function 

1.2 Gyro Electronics, ackage 

1.2.1, Outline drawing including connector locations 

,1.2.2 Weight, C.G. and inertias 

1.2.3 Mounting points and tolerances 

1.2.4 Physical description of mounting interface 

1.2.5 Interface connector type and orientation 

1.3 Interconnecting Cable 

*3.1 3-D shale and size 

1.3.2 Weight, C.G. & inertias 

1.3.3 Support Requirements 

2.0 THERMAL 

.2 

2.1 Gyro 

2.2 Electronics 

t. 

3.0 CABLE SPACE ALLOCATIONS 

3.1 Pitch interconnecting cable 

3.2 Roll intercpnnecting cable 

3.3 That Cable 

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3. 0 Selected Design Approach Integrity 

3.1 Error Budgets 

3. 1. 1 Introduction 

The performance of the telescope depends upon many factors. In order 

to control these factors, analysis has shown that the following error budgets are 

required: 

a. Fabrication and alignment error budget: establishes the 

mechanical, structural and thermal effects on optical element 

fabrication and alignment which disturb the aberration balance in the 

optical design of the telescope. 

b. Pointing Error Budget: analyzes those factors which will cause the 

telescope to be aimed inaccurately. 

c. Focus Error Budget: analyzes those factors which will cause defocusing of 

the telescope image. 

3. 1.2 Error Budget Status 

The fabrication and alignment error budget is partially completed. The 

fabrication and alignment tolerance sensitivities for each optical element are stated 

in Section 3. 6. 5 Figures 2, 5 and 6. These sensitivities must now be related to the 

structural, mechanical,and thermal tolerances which will govern the design, 

fabrication, installation, and use of the telescope. The completed portion of this 

analysis has developed the optical sensitivities of the elements related only to the 

optical design and performance considerations. The remainder of the analysis, yet to be 

done, will transform optical tolerances to thermal, mechanical,and structural 

tolerances which are needed for the overall system design of the Acquisition Optics. 

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The pointing and f ocus error b udgets have not been formally promulgated.. 

However, some of the factors which will be part of these budgets have been investigated such 

as defocus during zoom and magnification change (Section 3. 6), defocus due to 

slant range change (Section 3. 5. 4) , and alignment techniques for reducing the 

pointing error (Section 3. 5.4). The formal issue of these budgets will be forthcoming 

in the near future. 

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3.2 Mass Properties 

3.2.1 Weight 

The weight comparisons shown below and on the following tables are 

based on data relating to spec. EC 331 in one column and spec. 905850 

in the other. The listing under spec. EC 331 is based on the design 

approach Itek used to establish the original weight budget of 153 lbs. 

The other column corresponds to calculated and actual data of the most 

current layouts, details, catalogs, vendor supplied parts and particular 

selected materials. 

WEIGHT SUMMARY. 

SPEC. EC331'SPEC. 905850 

ITEM DESCRIPTION WEIGHT LBS. WEIGHT LBS. 

Telescope Assembly 70.75 81.00 

Window - Glass only 4.00 4.25 

External Fold Mirror Assembly 14.75 15.25 

Sun Sensor .50 1.00 

Tracking Pedestal Assembly 61.00 57.00 

Shroud Assembly 2.00 23.50 

Total for One AO Subsystem 153.00 182.00 

X 2 X 2 

Total for Two AO Subsystems 306.00 364.00 

Total Weight Budgeted 306.00 Not established 

"Note" If gimbal inertias are to be met per specification, additional trim 

weights totaling 33 lbs., (16.50 lbs. each "AO" Subsystem) are tentatively 

required. The Spec. 905850 should then be 198.5 X 2 = 397 lbs. total. The 

graph and tables in section 3.2.2 show pitch and roll gimbal inertias relating 

to the present design. 

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3.2.2 Gimbal Inertias 

3.2.2.1 Pitch Axis Inertia 

The present preliminary design configuration has a pitch axis 

mass moment of inertia of 0.054 slug-ft2. The specified requirement for this 

inertia is 0.08 slug-ft2 minimum. To meet this specified inertia would 

require the addition of approximately 2.0 pounds of trim weight. 

3.2.2.1 Roll Axis Inertia 

The roll axis mass moment of inertia is a function of pitch gimbal 

angle. The variation of roll inertia with pitch is presented in Figure 3.2.2-1. 

This figure shows that the present minimum weight design is considerably 

below the specified minimum inertia and that 16.50 pounds of trim weights 

would be required to meet this requirement. 

EC;IAL HANDLING SEEP t3. 2-2 
PAGE 

REPORT NO 

PROJECT NO 

UNIT SERIAL NO 

BY 

CHKD BY 

REVISED 

Itek 

ITEK CORPORATION 

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3.3 Power Budget 

The present sub-system power budget is 117 watts peak. Owing to the 

characteristics of the primary power system, Itek is presently constrained 

in peak power but not the long term average. 

A summary of the Subsystem power consumption by functions is shown in 

table 3.3-1. These power consuming items are isolated by groups that can 

occur as simultaneous demands on the vehicle power bus. The non-peak powers 

are also controlled to minimize short duration spikes, with their attendant 

poor utilization factors. 

The principal power consuming load is the roll gimbal torquer. It is 

shown in section 3.5.3 that the roll torquer is selected on a peak power basis. 

The allocation of power to each item, cross checking against the weight budget, 

and subsequent refinement is a continuous trial and error procedure. 

The power consumption calculations for the various activities are 

presented in the analysis section under the electrical design description 

of each mechanism. 

SPECIAL HANDLING --SteltET3.3-/ 
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SPECIAL HANDLING -SEC-RET2. 

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3.4 'RELIABILITY 

3.4.1 Reliability Program Status 

The status of the reliability program tasks is presented in 

terms of the Reliability Program Plan R-107 with schedule 

revision 26 July 1967. The reliability program activity 

has been reviewed on three occasions with the contractor 

reliability representative. The first was a program audit 

performed during the week of 17 July 1967; the second program 

review was during the TD Meeting, 17-18 July 1967; the third 

review was on 7 Sept. 1967. The reliability program effectiveness is also measured against the status of action in response 

to the audit. A copy of the audit status report dated 13 Sept. 

1967 is included. 

Part Selection and Application 

Schedule - March 1968 

Status - Initial stages 

Action - 1) Preliminary list given the customer 

representative for review. 

2) Pin lite miniature incandescent lamps. 

3) Pyro devices 

4) Cabling, flat with Kapton Insulation 

5) Encoders 

Part Qualification Specs/Requirements 

Schedule - Sept. 1967 

Status - 90% complete 

Action - Contract review to establish the requirements for part qualification. 

Burn-in and Screening Specifications 

Schedule - Oct. 1967 

Status - Recommended method submitted with program 

plan. 

Action - Request contractor guide to burn-in and 

screening requirements. 

Design Standards 

Schedule - Jan. 1968 

Status - 50% complete 

Action - Prepare standard parts, materials, and 

P c NO{ use sign 
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Traceability (program requirements procedure) 

Schedule - Oct. 1967 

Status - 90% complete 

Action - 1) Developed procedure for traceability (RE-OP-1) 

2) Submitted project policy for implementation of 

traceability procedure. 

FMEA 1st 

Schedule - Encoders 

Brushless MotorsOptical ElementsBearings,Gimbal - 

Data Display - 

Scanner AssemblyDoor Mechanism -

Window 

18 Aug. 1967 

18 Aug. 1967 

1 Sept. 1967 

1 Sept. 1967 

8 Sept. 1967 

22 Sept. 1967 

6 Oct. 1967 

15 Sept. 1967 

Status - First analysis complete for PDR input(15 Sept. 1967.) 

Action - Review and up-date for 2nd. report. 

RFMA lst 

Schedule - for PDR Report 15 Sept. 1967 

Status - complete 

Action - Review and up-date in preparation for 2nd Report. 

Vendor Reliability Program Control 

Schedule - Program Requirements - Jan. 1968 

Audit - Feb. 1968 

Liaison - Sept. 1968 

Status - Initial stages 

Action - 1) Reliability requirements for encoder established. 

2) Preliminary survey of encoders vendor's facility 

performed. 

3) Preliminary specifications for brushless torquemotor written(including the reliability requirements.) 

Training 

Schedule - November 1967 

Status - 50% complete 

Action - Training has been informal presentation of reliability 

concepts and program requirements with individual design 

engineers. 

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Maintainability 

Schedule -

Status -

Action - 

Interface (prime responsibility of System Engineering) 

April 1968 

- initial stages 

- The prinicpal inputs will be as a result of performing 

the other reliability tasks (FMEA). There have been 

inputs to systems engineering in the areas concerning 

ease of operation and complexity of operator tasks. 

responsibility System Engineering) 

- March 1968(Inputs) 

- Initial stages 

- The FMEA tasks has resulted in identifying several 

possible safety hazards which are transmitted to 

system engineering for evaluation. 

(prime responsibility System Engineering) 

April 1968(Input) 

Initial stages 

Reviewed program plan and furnishing preliminary inputs 

resulting from FMEA. 

Human Factors 

Schedule 

Statue 

Action 

Safety (prime 

Schedule 

Status 

Action 

Reporting 

Schedule - periodically 

Status - up to date 

Action - weekly program status reports. 

SPEC,IAL HANDLING -Stetif-T- 3.11-3 
Itek 

To: J. Boh 

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INTEROFFICE MEMORANDUM 

Date: 13 September 1967 

Page 1 of 3 Pages 

Facility: Burl. gll 349-67-487 

From: E. F. Powers Facility: Burl. Pll 

Subject: Status of Reliability Action Resulting from Audit 

The customer reliability audit has been sub-divided into 31 

separate action items. The status of 11 September 1967 is as 

follows: 

A.) 14-have been closed out as completed 

B.) 11-are in the final stages of preparation 

C.) 1-is in the initial. stages of preparation 

D.) 5-action has not yet started 

Below is a detailed accounting of the categories above: 

A. Completed; 

1. Reliability included on PDR adgenda 

2. In (3) separate areas of the audit restricted activity 

was noted. 

3. TR873-74 is being used as the RFMA procedure. 

4. Program examples of the RFMA were reviewed (rough cut 

of PDR input). 

5. Program examples of the FMEA were reviewed (rough cut 

of PDR input). 

6. Project policy for parts and materials control by. 

Reliability. 

7. Program example of supplier reliability requirements 

(encoder). 

8. Reviewed schedule for incompatability between supplier 

reliability requirements and long lead delivery schedule, 

9. The encoder SOW requires the supplier to conduct PDR and 

participatt in Itek's CDR & FACI. 

10. Traceability procedure is forMalized. 

11. Safety plan defines reporting of safety incidents (FMEA procedure also includes identifying potential safety problems.) 

12. Open failure analysis policy established for the project. 

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349-67-487 

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B. Final Stages 

1. CDR standard procedure being revised to require reliability 

participation, Responsibility - Central Rel. 

Completion Date: 1 Oct. 67 

2. FMEA procedure. Responsibility - Project Rel. 

Completion Date: 1 Oct. 67 

3. Communication like for problem areas (form in process). 

Responsibility - Project Rel. 

Completion Date: 15 Oct. 67 

4. Requirements for a vendor survey procedure was referred to in (2) 

separate areas. There is now a draft of this procedure. • 

Responsibility - Central Rel. 

Completion Date: 15 Oct. 67 

5, Traceability program plan, Responsibility - Project Rel. 

Completion Date: 15 Oct. 67 

6. Calendar life study to be part of the FMEA study (see draft 

procedure). Responsibility - Project Rel. 

Completion Date: 1 Oct. 67 

7. Failure reporting and analysis procedure in final draft form. 

Responsibility - Central Rel. 

Completion Date: 15 Oct. 67 

8. Reliability role in failure reporting and analysis is defined in 

procedure. Responsibility - Central Rel. 

Completion Date: 15 Oct. 67 

9. Reliability position in failure loop (see B7) 

Responsibility - Central Rel. 

Completion Date: 15 Oct. 67 

10. Failure reporting and analysis policy during development testing. 

Responsibility - Central Rel. 

Completion Date: 15 Oct. 67 

C. Initial Stages 

1. The non-standard part program responsibility is being transferred 

from QA to Reliability. Several books of standards have been 

prepared for distribution to the design team. 

Responsibility- Cen. Rel./Pro. Rel. 

Completion Date; 1 Nov. 67 

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Reliability 

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349-67-487 

Page 3 of 3 Pages 

D. Action Item Not Yet Started 

1. Procedure for submitting failure reports to customer. 

Responsibility - Central Rel. 

Completion Date: 15 Nov. 67 

2. Procedure for submitting failure analysis reports to customer. 

Responsibility - Central Rel. 

COpletion Date; 15 Nov, 67 

3. Procedure for assuring 12 hour notice of failure during qual. 

test (TWX). Responsibility - Central Rel. 

Completion Date: 15 Nov. 67 

4. Procedure for reliability data collection and reporting. 

Responsibility - Central Rel. 

Completion Date: 15 Nov. 67 

5. Reliability education plan. Responsibility - Project Rel. 

Completion Date: 15 Nov. 67 

Several of the action items above are to be covered by a single 

procedure. 

In several cases more than one of the above action items will be 

covered by a.single procedure. There are actually (8) procedures 

involved in closing out the open items above. 

A. Van Sickel 

EFP/mb 

DISTRIBUTION: A. L. Wright 

M. Nikonchuk 

T. B. Robinson 

A. Van Sickel 

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3.4,2 Reliability Figure of Merit Analysis 

3.4.2.1 Abstract 

The first RFMA has been performed for the complete system. The 

source of the design data was preliminary drawings and sketches with 

estimated stresses. Failure rate data was taken from MIL HDBK 217A 

and FAIADA SP 63-470 Vol. 1. Application (K) factors and prediction 

methods are in accordance with TR 873-74. 

The results of this analysis shows: 

99.60% probability of achieving a successful 50 hour mission with 

all controls operating automatically. 

99.81% probability of achieving a successful 50 hour mission with 

automatic or manual control. 

The following system breakdown shows the assemblies which contribute 

most significantly to the total predicted unreliability with their allocated MTBF's and per cent contribution 

MTBF % 

Optical Encoders 46,000 10 

Solar Blanking Assembly 27,400 16 

Power Changer 37,200 12 

Cue Assembly 36,500 12 

Protective Shroud 12,600 35 

85 

The Solar Blanking, Power Changer and Cue Assembly have relatively 

high failure rates principally because of the brush-type fractional horsepower motors planned for use in these assemblies. The Protective Shroud 

contribution results from the pyro lock devices with no redundant backup and the brush-type drive mdtork. The MTBF of the Optical Encoders 

is shown for series configuration (no redundant path). The calculation 

of system reliability does however reflect the redundant capability. 

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3.4.2.2 Mathematical Model for Telescope Reliability 

There are several states of system performance that can be assessed. 

Presented here are the two (2) models fora successful (or partially successful) mission considered most meaningful for this equipment. 

General Model 

R = P

A

•PB.PCD•PE

oPF.13G

.PH 

I. Fully operational with all automatic functioning (redundancy is 

considered operating except for the encoder). 

R

I = [ {A1A(A1B2 2 )} 1A5A(A5B + A513 01 2]. 

[ 81.132-133]. [ C1.02] • [Dl.D2] • [El.E2 • [Fl.F2]. 

2 

• Ge (41) • 

Where the symbols AlA, A1B, A2, etc. are probabilities of 

success and subscript (1) indicates the probability of (1) failure. 

II. Operational by either automatic or manual controls (degraded mode). 

R

II = [{A1A(2A1B-A1B2

)}2

.A3•A4 1A5A(A5B+A5B1)12] 

[B1(B2+B3-B2.133)] [C1(02+03-02-03)].[D1(D2+D3-D2.03] 

[E2+E3-E2 E3] [Fl(F2+F3-F2 F3] [G] ti2H1-(H1)2

]H2 

The success probabilities of the individual terms in the above 

expression are determined as follows: 

-X(AlA) T (AlA) =2A5BTe-AA5BTA1B 

PA1A = e A5B1 

where A(A1A) = the expected device failure rates (taken from 

MILHBK217A and FARADA) within the useful life of the item; and 

T(A1A) = the expected operating time of the item when the telescope mission time (period of use) is 50 hours. 

The MTBF of the telescope is determined from the mathematical 

model expressing reliability (R) as follows: 

00 

= f

o 

R(t)dT [1] 

3. y - 
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SPECIAL HANDLING ---SEGREFCondition I 

R(T) e

-v•(le-w

-e

-2w)

2

(2e-x

-e

-2x)

2(2e-y-e-2y) [2] 

where v - E2T for all series elements 

w AA1BT 

x = A5BT 

AHT 1 

Condition II 

The form of the expression for"11,0 in condition II is the same 

as above except the manual over-ride a6fige several terms in V to 

approach zero. Therefore, 

R II = R(T)I 

(T) 

e

-v [3] 

where v' is the sum of the terms that vanish due to the 

manual overide. 

It should be noted that the MTBF in either conditions I or II 

is nOt simply the inverse probability operation Tir = 11-ln R(T) 

because of the redundant operating modes. 

Not all of the functional elements of the telescope are required to operate continuously during the period of use for the 

telescope. The following duty cycles have therefore been assumed: 

Assembly Duty Cycle Mission Time 

(A) Tracking System 100% (50 hours) 

(B) Sun Sensor and Blanking 20% (10 hours) 

(C) Low Power Changer 25% (12.5 hours) 

(D) Cue Mirror 50% (25 hours) 

(E) Prism 100% (50 hours) 

(F) Zoom 50% (25 hours) 

(G) Data Display Assembly 40% ( 20 hours) 

(H) Door Release 50% (25 hours) 

SfrtLIAL HANDLh:.C.3 
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SPECIAL HANDLING 4E-6RET7 

El 

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10 

• 

p

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8. 

co 

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8 

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04 . describedasfollows: 
SPECIAL HANDLING -SEGREf 

CONDITION 3. 4- // SPECIAL HAIWL'i'l 

4 

M in 

2; 4 

EN CO DER 

Tracking System 
3.4 - 

Tracking System 

C 

0 

cc 

success 

Co

ndition II (degr 

O a 

J 

SPECIAL HANDLING --SEGRETSPECIAL HANDLING SECRET. 
SPEC■ AL HANDLING . .7.crIET. 7

— — — 

Solar Blanking 

LowPowerChanger Assembly/, 

Prism Assembly/, 

Ts 

J 

PB 

B1•(B2+B3-B2•B3) 

LL N 

—fl _1 

> 0 

a. 

a. 

0_ CO 

1.11 O_1 

L1.1 

Z CC 

LC1AL 1 AA). 
PROTECTIVE SHROUD 

Condition I Condition I 

SPECIAL HANDLING 

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3.4.2.3 Calculation of Telescope tg1ieigT11ty 

The calculations below are based upon the support failure rate data 

attached and the mathematical model. 

Condition I Al

P - (A1A•AlB2 )2 = e -(2AA1A +4AA1B)T 

AlA - 0,AA1D='231; T = 50 

Condition II 

P

Al = [AlA (2•A1B-A1B2)]2 

= eAA,A

T

(2e AA, T

-e

-2XAlBT

) 

When AT is small 

e 

 , 1-AT 

AALA 0 

- .999954: 

Therefore, PAl = 2(1-AA1BT) - (1-4A1ST)2 

T = 50 hours XA1B = 0.231 x 10

-6 AT = 12 x 10

-6 

1-AT = .999988 (1-AT)2 = .999976 

1.999976 - .999976 

PA1 = 

P

Al 

m 1.0 1 

p = p 

A2 Al 

A3-Bearings 

P

A3 = 1-AA3T X

A3 = 2.184 

AT = 109.2 

T= 50 

TP .999890 

A4- Misc 

P

A4 = 1- A4T XA4 - 1.310 T = 50 

AT = 66 x 10-6 1PA4 = A99934; 

A4 -Pyro 

pA4A = 2e T -

e-2AA4A

T 

= 27.30 AT = 50 AT = 1365 2XT=2730 

1.997272 - .997274 

PA4A = PA4A " 999998 

SPLC!;-1 HAr 

1.) -Scan Assembly (A) 
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A5 -Encoder 

Standby 

2 2 

P = [A5A (A5B + A5B )]2 

= ((1 -XA5AT) [1-

(X

A5B

T)]} 

A5 1 2 

ASA = 1 (disc) 1A5A 

= 0 X

A5B = 21.846 T=50 

XT = 1092.30 x 10-6 (AT)2 = 1.192 x 10

-6 

P

A5 = (1- .6 x 10-6)

2 

ZA5 ' . I 999998' 

Operating. 

P

A5 = (2e-XA5BT 

-e

-2XA5B)2 

= 2(1-AT) 

P

A5 = (.998908)2 - (.998908)2 

P

A5 = (1.997816 - 997817)

2 

Scanner Ass'y Condition I 

- (1-1T)2 

.999948 

P

A 

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A2 P

A3 PA4 PAS P.= .999774 , 

Scanner Ass'y Condition II 

PA = PAl.1)A2.PA3.PA4'PAS 

= (1) (1)(.999890)(.999934)(.999998)(.999998) 

1 PA= .9998201 

2.) Solar Blanking (B) 

Condition I 

PB = 1-365 x10-6 

`

PL .999635 I 

.Condition II 

P

B = B1 (B2 +B3-B2 B3) but B3 = 1 and all mechanisms 

required for automatic are also required for manual. 

P

B = 1-XB1T AB1 = 16.593 T=10 

P

B = 1-35 x 10-6 1 PB= .999834 1 

-474i4ti47 

3.4/-/4 

PB = Bl.B2 = e-XB

T 

X

B = 36.516 x 10-6 T=10 
3.) Low Power Changer (C) 

Condition I 

P - (C1)(C2) - e

-ACT A

C - 26.874 T-12 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SPECIAL HANDLING --9E-C-RET7 

P

c 

= 1 322 x 10-6 Pc- .999678 I 

Condition II 

= PC . = 1-1 1.C1 C1T 6. 952 T = 12 

= 1-83 x 10-6 ! PC = .999917i 

4.) Cue Mirror (D) 

Condition I -,,T AD = 27.370 T=25 

PD = D1•D2 = e 

PD - 1-A T =1- 684x 10-6 PD = .999316 i 

Condition II 

PD = 1-XD1T X DI = 7.448 T=25 

PD =1•-ADI T = 1-186 x 10-6 1 Pc= .999814 1 

5.) Prism Assembly (E) 

Condition I 

E XE = 5.212 

T 

PE = E1.E2 - e T=50 

PE = 1-AT = 1- 261 x 10

-6 PE.999739 -7 

Condition II 

PE = 1-XEl

TT=50 A E1 = 4.981 

PE = 1-249 x 10-6 .999751 

6.) Zoom And Eyepiece Assembly (F) 

Condition I -AF

T 

P

F = Fl-F2 = e 

P

F = 1-XF

T = 1-135 x 10-6 

Conditon II 

P

F =

FlT AF1 = 5.172 T=25 

P

F - 1-129x 10-6 PF= .9998711 

SFECIAL HANDLING 

XF = 5.403 T=25 

P = .999865 ! 

3 -1 7 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SPECIAL HANDLING 

7.) Data Display (E) 

-AE

T 

PG = e

G = 23.834 

P

G -1- 477x 10-6 

= .999523 j 

8.) Shroud (H) 

Condition I 

P = (H1)2

•112 = e-(2iH1 + AH2) T 

Conditinn,II 

-2AH1T -2AplT -XH2T PH1:(2H1 - (HI)2

jH2 = (2e -e )e 

A H1T =546 x 10 -6 XH2T = 750 x 10 -6 

PH = (1.998908 - .998909)H2 (, PH = .999241 

9.) Systems Terms 

Condition I 

Ps = 

Condition II 

PS TrPr—r" PH 

P

S = .996349 

P

s 

= .998426 I 

S L SEC1(4 

T=20 

A

H1 = 21. 844 1

H2 = 29.996 T=25 

-6 

X T=1842 x 10 1 PH- .998160 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SPECIAL HANDLING SECRET 

Apportionment of System Reliability 

Xx10 6 MTBF 

Pitch and Roll Encoders 

(for a single non-redundant 

path) 

21.846 '21.846 9.64 

Scan Motors .340 .15 

Solar Blanking Assembly 36.516 27,385 16.12 

Power Changer 26.874 37,211 11.86 

Cue Mirror Assembly 27.370 36,536 12.08 

Prism Assembly 5.212 2.30 

Zoom & Eyepiece 5.403 2.39 

Data Display 23.834 41,957 10.52 

Protective Shroud 79.136 12,637 34.93 

226.531 100.00 

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NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SPECIAL HANDLING 

3.4.3 Failure Mode and Effects Analysis 

.3.4.3.1 Introduction 

Three submissions of FMEA reports are planned for this contract. 

Contained herein is the first report which is deliverable for PDR. 

This malydis is based upon preliminary design information since detailed 

drawings and specifications are not yet available. Subsequent analysis will be refer.:enced directly to the applicable drawings and specifications using the family tree, system block diagram and reliability 

block diagrams as guides to organization. The FMEA report is concentrated in the area of critical functions and long lead items. An 

analysis was performed to determine critical functions, 

then each such function was analyzed. 

The detailed report was summarized into areas representing potentially critical and major problem areas, potential safety hazards, a 

preliminary list of life limited devices and possible added compensations for potentially critical or major problem areas. The detailed 

analysis report is augmented with narrative and block diagrams where 

necessary for ease of understanding. 

Reference document no.61SD52 was used as a guide in the performance of this analysis. A draft procedure for FMEA is complete which 

assigns responsibility as it relates Itek operations and includes 

consideration of life limited devices and safety hazards but in other 

respects is in accordance with 61SD52. 

The following criteria was used to categorize assumed failure mode and 

effects: 

Safety and/or Hazard Modes - in accordance with MIL S 38130. 

Failure Class - the determination of the failure impact is based 

upon the proper operation of the optical instrument as a tool for obtaining useful 

visual data. 

3. -90 

SI~ LCIAL HANDLING SECRET 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

bi:EC,;AL HANDLING 

3.4.3.2 Potential Critical Problems 

Scan Without this function, the system is completely inoperative. 

This is a complex function having a significant probability 

of occuring. 

Window This forms part of the vehicle pressure integrity. A backup is provided in the event of excessive leakage but because 

of crew safety, this assembly is considered critical. (The 

telescope main barrel and objective lens assembly are the back-up.) 

Optical Path Any disturbance or condition which causes the optical parargeter (i.e., distortion, resolution, focus, etc) to be 

severely degraded will result in mission abort (for the 

telescope). The probability of this occuring in not great, 

but the impact would be critical. 

Door A mal-function of the protective shroud which prevents its 

opening (or restricts) results in an aborted mission. The 

complexity of the mechanism with pyros and drive trains results in a significant probability of this occurance. 

Solar Blanking. If the response time of this mechanism is slow (or inoperative) 

serious injury to the operator may occur. Although the mechanism is simple and has a low probability of occuring,since 

failure would directly affect the safety of the operator, it 

is considered a critical item. 

Cue Mirror If the switch contacts are welded, it will cause the Geneva 

pin to hit a mechanical stop with each index. If the impact 

is strong enough, the pin eventually could bend or break, 

disabling the Cue Mirror from any control, even manual. 

1-1A1\;1..L.,,0 SL 3.4-3/ 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SPECIAL HANDLING -SECRET" 

Potential Critical Problems (cont.) 

Window Assembly The window seal is considered of major importance even 

though there is a back-up first element seal, since complete mission abort may be required in the event of failure. 

This sial ii'the Allionsibility/bf'the vehicle tOrittor. 

3.4.3.3 Potential Major Problems 

Door Assembly 1. If one motor fails, the door cannot maintain a strong 

seal when closed. Thus, contaminants may enter whictrmay 

degrade the optical elements. 

2. If Pyro release does not work, and one motor fails, 

it could interfere with performance. 

3. If motor and its pyro both fail, the door could be jammed 

in any position. If not open wide enough to allow scanner 

to work, it would be a Critical failure. However, 

two unique failures are necessary before this condition 

could occur. 

4. If motor A failed and pyro B were activated, the door 

drive would be completely inoperative and the scanner 

could not work. If the door were opened wide enough for 

the scanner to operate, the impact of the failure would 

not be as great, but the door could not be closed and the 

scanner would not be protected from unfriendly environment. 

fzi3yi-o,p were then'activated, the door wouldfail safe - 

open, however, the scanner would still not be fylly protected. 

- 32 

SVLCIAL HANDLING ---SEeRel" 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SPECIAL HANDLING 

Lo Power Changer 

1. If a bearing should freeze so that the manual control were 

ineffective, and it froze in a mid-position it would cause 

excessive distortion. 

Brushless Motor Torque (2 winding type used in Pitch and Roll drives) 

1. Open winding. The second winding provides enough torque to 

meet the spec. but the resultant slower response is a degradation in performance. 

2. Partial or complete short. Same as above. 

3. Both windings fail. The possibility of two failures occuring 

puts this in the major problem area. 

Gimbal Bearing (either pitch or roll) 

1. If the bearing has high friction, is sticky, jumps, or brinells 

the performance will be degraded. 

Scanner Launch Locks & Pyros 

1. Both redundant pyros do not fire. 

Sun Sensor 

1. Both redundant sensors open. 

2. 

I/ " shorted. 

3. One sensor shorted. 

SrECIAL HANDLING SCC 

3.4-33 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SPECIAL HANDLING 

3.4.3.4 Compensations for Potential Problem Areas 

Cue Mirrors 

1. Two switches in series redundancy 

2. Drive Geneva slower to lessen pin impact, in case of welded 

switch contacts, so pin won't bend. 

3. Drive mirror via slip-clutch, while manual control connects 

to mirror (Push-to-operate knob). 

Window 

(If window and first element seals both leak excessively) 

1. Pressure sensor between the window and element to indicate loss of pressure. 

Door Assembly 

1. Redundant pyros in each motor linkage 

2• Redundant mechanical drives 

3• Redundant switch 

4. Operator control of motor power and direction. 

Brush Type Motor 

1. Redundant brush leads. 

2. High enough armature resistance or other current limiting 

component. 

3. Wound - field motor in place of PM type. 

4. Threshold sensor (current) 

5. On - off switch 

6. Circuit - breaker 

Blanking 

I. Redundant springs, either of which is able to close the 

shutter fast enough. 

HANDLik;G SECRET 
MIRO APPROVED FOR 

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SPECIAL HANDLING GECRET 

2. Have the redundant sun-sensors isolated from each other, 

so that if one is shorted, it does not affect the success 

of the other. 

3. Have one of the four filters dense enough so that the 

operator can safely use the manual control to open the 

shutter, (or white cardboard etc). 

Specify a sequence of operation before using the telescope in 

order to prevent inadvertent exposure to sun (e.g. insert 

dense sun filter before use or have image projected onto a 

screen behind eye piece before viewing). 

Si-LCIAL HANDLING SECRET 

3.'-3c 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SPECIAL HANDLING -SEeltE-T3.4.3.5 Life Limited Devices 

A preliminary list of items that could be life-limited 

1. Lamps 

2. Brushes 

3. Epoxy 

4. Lubricants 

5. Adhesives 

6. Switches 

7. Paint 

8. Insulation 

Definition of Life-Limited: 

1. Shelf life less than five years. 

2. Age life less than one year. 

3. Operational life of less than 500 hours. 

3.4.3.6 Possible Safety Hazards 

Window 

If both the window and first element seals leak excessively, the rate 

of pressure loss may exceed safe conditions. 

Blanking Shutter 

The criticality of this device has been covered elsewhere. However, there 

should be an operator safety procedure when using the manual control to 

open the shutter. 

3.#- 36 Si tL ML HANDLING ---S.E&RET- 
0 

0 

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a_ 

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PREP. BY E. F. Powers 

DATE 9-8-67 FAILURE MODE EFFECTS PROJ ECT NO. 9300 TA s k OPTIC/ALSYSTEM 

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NRO APPROVED FOR 

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SPECIAL HANDLING SECRET 

FMEA Index 

Detailed FDA's for individual subassemblies are presented 

in the following sections: 

Tracking Assy 

Fix Fold Mirror & Mount 

3. 7. 7. 1 

3. 8. 6 

Protective Shroud 3.9. 7.1 

Telescope Assy 3.10. 2. 7.1 

Pechan Blanking & Cue 3.10. 3. 7 

Zoom Assy 3.10. 4. 7 

SPECIAL HANDLING 4C-GRE-1-- 
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SPECIAL HANDLING --5-E646T3.5 STUDIES 

3.5.1 Protection Shroud 

This section presents the development of the current baseline for the 

protective shroud. 

3.5.1.1 Original Baseline 

The design concept baseline for protection of the AO external hardware 

from the degrading effects of exhaust impingement was given in Technical 

Proposal 3010-66-052, 28 November 1966, and Addendum 3010-66-073, 22 December 

1966. Figure 3-21 of the proposal is reproduced in Figure 3.5.1-1 for 

reference. 

This configuration calls for the on-orbit ejection of a portion of the 

aerodynamic fairing with the remaining portions providing partial sun 

shielding and exhaust product baffling. The bonnet contained a spring 

loaded door which acted as a sun shield when open and provided a labyrinth 

or "soft" seal when closed. As stated in paragraph 4.0 of the referenced proposal 

addendum, this approach was considered adequate at that time. 

3.5.1.2 Shroud Configuration Development 

While the original baseline concept was considered adequate, there was 

considerable concern, both at G.E. and Itek, that the contamination problem 

might be worse than anticipated. During the first 10 to 12 weeks of the 

program (Jan. - March 1967) repeated attempts were made by Itek and GE to 

obtain definitive exhaust products data (see 3.5.3.5). As a result of this 

concern and lack of data,a development cycle was initiated at the April 

TD meeting. (Refer to table 3.5.1-1 for descriptions of the configurations 

discussed below.) 

Configurations A through G were presented at the April TD meeting. 

Since only configuration D provided positive sealing, Itek was directed to 

proceed with that approach. 

At the May TD meeting, configuration El was presented. Direction was 

received to initiate a detailed shroud study. (See Addendum 3.5.1-A) 

At, the 12 May meeting, configurations F1 through H were presented. 

Itek was directed to proceed with configuration H which had minimum impact 

on the position of the AO window proposed by DACo. 

At the 18 May meeting, configurations J through L were presented. Since 

configuration L afforded the minimum violations of the design requirements, 

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SFECIAL 

Itek was directed to proceed with this. 

At the 25 May meeting with GE, AF and Aerospace, configuration 

M and N were presented. Since configuration N met all requirements except 

the horizon scanner interference, for which a system solution appeared 

possible, Itek received direction to use this as the new baseline. 

3.5.1.3 Current Baseline 

The current shroud baseline concept is shown on drawing 114400 and is 

discussed in detail in section 3.9. 

firtI'%L,LigVJ 

3. 6-- z 
JA 
—NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Vii2(AL HANDLING SECRET 

BY: C.. SU Q. E...77 e- TITLE: 

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Frontal Area 

Surface Area 

WEIGHT(lbs.) 

ELEC.POWER (watts) 

COMPLEXITY 

; RELIABILITY DEGRAD. 
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TABLE 3.5.1-3 

(Presented at the. May 24th Meeting) 

SHROUD PARAMETERS 

ItMII NI! 

INLINE OUT OF LINE 

Max. Protrusion 

Deployed 25.00 in. 24.88 in. 

Stowed 15.65 in. 15.65 in. 

Frontal Area 

Deployed 3.9 sq. ft. 3.6 sq.ft. 

Stowed 2.1 sq. ft. 1.8 sq. ft. 

Radiator Blockage 

6.4 sq. ft. 4.5 sq. ft. 

Surface Area 18 sq. ft. 18 sq. ft. 

Weight ' 10 lbs. 10 lbs. 

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9300-67-X130 

COPY NO. _ 

2 PAGES 

-EeREV SPECIAL HANDLING 

' ' 3 . - 

5 May 1967 

To: A. L. Wright, Manager, Project 9300 

From: J. E. Brogan, Subcontract Project Manager 

Subject: Investigation of External Interface Problems 

1. Background 

The current design of the externally-mounted acquisition optics 

presents the following interface problems: 

- interference of the shroud with the viewport and molecular sieve. 

- excessive radiator coverage and blockage. 

- optical interference with the horizon scanner field-of-view. 

- excessive protrusion from surface of Lab Module. 

Itek is directed to perform investigations aimed at the minimization 

of the above problems. 

2. Investigation Design Goal9 

The design goals for the external installations are as follows: 

a. Maximum Protrusion 

The maximum protrusion of the stowed system shall not exceed 

15.65 in. from the radiator surface. The follqwing constraints, 

in descending order of acceptance, are delineated: 

- The radiator can be "cut-away" in the area of mechanical 

interference with the scanner. 

- Vignetting in obliquity from 35° to 45° is permissible on the 

vehicle side only. 

- The forward scan field can be reduced from +70° to +50°. 

- The aft scan field can be reduced from -40° to -35°. 

SEGREVSPECIAL HANDLING 

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rog. n 

S .contac Project Manager 

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b. Viewport and Molecular Sieve Interference 

The shroud shall not interfere with the viewport and the 

molecular sieve outlet. 

c. Radiator Coverage and Blockage 

The surface area of the radiator which is covered and blocked 

by fixed and movable parts of the shroud shall be minimized -

at the expense of shroud design complexity as necessary. 

d. Horizon Scanner Field-of-View 

The shroud, in either the stowed or deployed position, shall 

not violate the horizon scanner field-of-view plus 1 inch. 

This study shall result in layouts and performance data of 

sufficient detail to permit reliable system decision making. 

The gimbal configuration remains at 9° total cant; i.e. the 

optical axis between the folding and tracking mirrors is 

oriented at 9° with respect to the roll axis of the OV. The 

roll gimbal axis is also oriented at 9° to the OV roll axis. 

3. Study with 9° Gimbal Cant 

When the above study is completed, similar results shall be 

provided for a design based on 9° gimbal cant. 

4. The study shall be based on the following schedule: 

12 May 1967 

19 May 1967 

25 May 1967 

First cut; trades identified 

Itek Recommendation/.s 

GE/AF/AS/Itek/DAC. meetifig at Radnor 

(tentative date) 

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3.5.2 Cant Angle 

3.5.2.1 Description 

Cant angle is incorporated into the AO system to increase the minimum 

roll tracking rate. By canting the tracker roll axis relative to the vehicle 

roll axis, the increase in minimum roll rate is achieved by a cross roll 

component of the vehicle forward velocity vector. 

The cant angle effects can be realized by either an inboard or 

outboard cant. The inboard cant, however, necessitates a tracking pedestal 

support of approximately twice the length of the outboard cant. 

Cant angle may be incorporated in two ways: 

a. Total Cant - when the tracker roll axis is coincident with the 

optical axis (between the tracker and fold mirror) and not 

parallel to the vehicle roll axis. 

b. Gimbal cant - When the tracker roll axis is not coincident with 

the optical axis (betewen the tracker and fold mirror) or 

parallel to the vehicle roll axis. For this cant scheme the 

optical axis between tracker and fold is parallel to the vehicle 

roll axis. 

3.5.2.2 Design Considerations 

Cant angle impact on shroud design was primarily aggrevating the 

maximum rro,rusion criteria as the inboard total cant moved the tracker roll 

housing outboard and the outboard total cant moved the folding mirror bezel outboard 

Inboard gimbal cant had the distinct disadvantage of severely cutting into 

the radiator. Outboard gimbal cant was most advantageous because: 

1) No radiator interference 

2) between pitch angles of +40° and +10° more than 35° 

roll towards the vehicle was realizable without vignetting. 

3)Gimbal pitch and roll total angular excursions increased from 55° in pitch 

to 58°, and 90° in roll to 103°. This angular excursion obviously meant 

restudying pitch and roll torquer selections. 

4) Mirror size was not a significant factor in cant method (inboard, 

outboard, total or gimbal) because when the tracker mirror would increase 

the fold would decrease a similar amount and vice versa. 

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3.5.2.3 Conceptual Layouts 

Cant angle concepts and layouts are listed in Section 3.5.1 

Drawing SK 905842 

indicates gimbal angles required to cover the target area with a 9° gimbal 

cant. 

3.5.2.4 Further Analysis 

Final vignetting and obscuration studies are still necessary. 

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3.5.3 Engineering Trade-off Studies 

The Work Statement, WS011 (3010-67-090), requires that certain 

engineering trade-off studies be performed. A verbatim statement of these 

requirements is as follows: 

"The Subcontractor shall perform trade-off studies to support the 

Acquisition Optics (AO) design. These studies shall culminate in reports 

which shall be prepared and submitted in accordance with DRL GE-MOL-S-115. 

Specific studies to be performed shall include, but not be limited to, a 

weight trade-off which shall consider the following: 

(a) Minimum weight of the fairing/scanner combination 

(b) Minimum added launch vehicle propellant weight to overcome the 

fairing drag during ascent. 

(c) Minimum added orbital vehicle weight for orbit adjust propellant to 

overcome the effects of the scanner drag both in the stowed and 

operating position. 

Related areas to be considered in preparing this trade-off study shall 

include: 

(a) Means of reducing the scanner envelope with minimum compromise to 

the optical, mechanical and thermal aspects of the design. 

(b) Means of protecting the optical surfaces and other operating 

components from the degrading effects of exhaust impingement 

emanating from the attitude control and orbit-adjust thrustors, 

and from the effects of meteoroid erosion. 

(c) Trade-off of torquer size and weight versus peak power requirements. 

The result of this trade-off study shall be a report which describes in 

detail the various trade-off factors and arrives at a scanner design approach 

which is optimum from the point of view of over-all system weight compatible 

with the other aspects of the design (e.g., optical, mechanical, electrical, 

and thermal." 

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3.5.3.1 Minimum Weight of Fairing/Scanner Combination 

To attain a minimum fairing/scanner weight the volume to encompass 

the external AO components must be minimized. Of the two major components 

on the exterior of the vehicle (fixed fold and scanner) only the scanner 

position could be changed significantly. Volume to be enclosed by the 

fairing is controlled dimensionally by: 

1. Length of optical path from the centerline of the fixed fold to 

the face of scan mirror, 

2. The protrusion of the equipment radially from the vehicle wall 

and, 

Y • 

3. The circumferential dimension required by the AO components 

To obtain a minimum distance from fixed fold to scanner, the system ° 

wasodesigned to maintain the no vignetting, no obscuration in pitch (+10 to 

+40 ) requirement and maintain the scanner pitch axis as close to the front 

face of the scan mirror as weight and balance would allow. 

It was readily shown in concept drawings of the "Protective Shroud 

Study" (section 3.5.1) that the maximum radial protrusion from the vehicle 

is dictated by the fixed fold bezel. The position of the fixed fold mirror 

however, is determined by the scan mirror line of sight requirements in roll. 

In the stow position the scan mirror offers little protrusion. 

The circumferential dimension is determined by the scanner pedestal 

mount spread at the vehicle wall, the mirror minor diameter, and the 

requirement of protection to be afforded the penetration fitting. 

The evolution and trade off of the above to attain minimum envelope 

without compromise of the design requirements and to incorporate mirror 

protection are discussed in sections 3.5.1 and 3.5.2. 

3.5.3.2 Launch vehicle propellant minimization study deleted per letter of 

20 April 1967 from R.G. Emerson to D. Jones (DIN 50099-164-2) 

3.5.3.3 Orbital adjust propellant minimization study deleted per letter 

20 April 1967 from R. G. Emerson to D. Jones (DIN 50099-164-2) 

3.5.3.4 Scanner Envelop optimization study 

This topic is related to section 3.5.3.1 and is discussed in its 

references. 
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61-LCiAL HANDLING --SE-C-RE-T3. 5. 3. 5 Exhaust Impingement Study 

In order to insure that the impingement of exhaust products for the translation 

thrustors will not be allowed to degrade the performance of the AO, a three-fold 

effort was conducted. 

First, an intensive search was made of open literature on contamination of 

optical surfaces in a space environment. The major sources were the Gemini 

Mid program Conference report (NASA SP-121) and the Attitude Control Rocket 

Exhaust Plume Experiment Final Report (AFRPL-TR-67-3) supplied by GE. This 

data was inconclusive. The interpretation of flight data is somewhat contradictory 

and the extrapolation from idealized test conditions questionable. Combustion product 

data was received from G. E. at the 2 February 1967 TEM; however, further specific 

data has beenunavailable from AF/Aerospace sources. 

Secondly, at the request of G. E. , Itek has proposed a cooperative effort to 

support the forthcoming Air Force test program. The initial proposal is shown in 

Addendum 3. 5. 3. 5-A. It is anticipated that further requests for participation 

will be made shortly by G. E. 

The third aspect of this effort is reflected inihe shroud design concept baseline 

described in Section 3.9. Due to the lack of firm definition of the exhaust hazard and 

as a result of the study detailed in Section 3.5.1, Itek proposed the current "positive 

seal" approach. At a meeting on 25 May 1967 and as a result of AF/Aerospace 

direction, G. E. directed Itek to implement the configuration shown on drawing SK905825 

(Configuration N). This resulted in the design concept being changed from the lightweight 

labrynth sealed shroud to a shroud completely enclosing the external components. This 

required an operational door which is tightly closed during translation thrustor operation. 

SPECIAL HANDLING SECRET 3.5-06 
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SPECIAL HANDLING BOS-COR-1300-67-097 

COPY NO..15.1. 

To: Distribution Date: 4 April 1967 

From: R. R. Heath Page 1 of 2 Pages 

Subject: Recommendations for Exhaust Impingement Experiment 

Scope ADDENDUM 3.5.3.5-A 

This memo presents preliminary recommendations for Itek participation in 

an experiment to be conducted by Air Force/DACo to investigate the effects I 

of translation engine exhaust on vehicle external material and devices: 

Since the experiment is not as yet well defined, the recommendations presented 

are quite general. All Itek participation will be through General Electric. 

Approaches 

There are two general approaches which could be taken. The first and most 

desirable, from a strictly program viewpoint, is to include a scaled model 

of the external AO hardware to be located appropriately in the exhaust 

path. The second approach is to fabricate a sample block containing optical 

and finish samples in several configurktions such that fundamental information could be obtained. It is strongly recommended that both approaches 

be implemented since this would yield maximum benefit to the program and the 

state of the art in general. Details of each approach follow. 

Scale Model 

The model, constructed to the scale of the experiment (probably 1:4), 

should include the two mirrors (fixed), a window, some supporting structure, 

the fairing or shield and thermal control finishes. In addition, it may 

be necessary to include temperature control to maintain the surfaces at the 

expected temperatures. Some study is necessary to determine how such things 

as opening size and location in the exhaust stream should be scaled since 

this may be a function of the pressure and mean free path in the test 

chamber. 

Sample Block 

The sample block should be designed to allow the sample to be mounted in 

three locations: 1) perpendicular to the exhaust stream, 2) parallel to 

the exhaust stream, and 3) inside a baffled enclosure. Each sample location 

would contain the following items: 

1. Aluminum surface mirror with no overcoat 

2. Aluminum surface mirror with silicon-monoxide overcoat 

3.S-17 

--SEMETIPECIAL HANDLING 

a. 
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Page 2 of 2 Pages 

3. Optical glass blank (probably BK-7) 

4. Thermal finishes 

These samples would be on the order of one inch in diameter. Consideration 

must be given to the shape of the blank since this will effect the exhaust 

flow in its vicinity. 

Handling Considerations 

The samples would he prepared at Itek and initial optical and thermal 

measurements made. They would then be enclosed in a suitable bag and/or 

container purged with dry nitrogen. All subsequent handling should be 

done under strictly controlled conditions. 

After the test, the chamber should be purged with dry nitrogen and the samples 

repackaged in their container which will again be purged with dry nitrogen. 

The samples should be returned in this condition to Itek for final measurements. 

R. R. Heath 

Pm 

Distribution: 

A. Van Sickel 

A. L. Wright 

-GEGRET/SPECIAL HANDLING 

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SPECIAL HANDLING -S-E-C-RE-T-- 

3.5.3.6. POWER CONSUMPTION VS. WEIGHT OF SCANNER 

BRUSHLESS DC TORQUE MOTORS 

This data is presented in satisfaction of section 1.1.1. (item C) of statement 

of work WSO11, dated 3 January 1967. 

A situation exists where a DC torque motor is used in an equipment in which 

weight, power, and energy must all be minimized. An important design consideration 

is optimum sizing of the motor with respect to weight, power, and energy budgets. It 

is shown that if the weight and energy budgets are not considered simultaneously, 

the overall design may stray from optimum. 

In the following descussions, it is assumed that there is a choice from among 

several motors that can satisfy the torque-speed requirements of a load. It is 

first assumed that the load torque can be developed independently of the available 

peak power; the peak power restriction is then added. 

The rationale behind the weight and energy budgets is assumed to be for purposes 

of minimizing total system weight of motor plus energizer. Accordingly, the most 

realistic criterion for sizing a torque motor under such conditions is to select a 

motor such that the total weight of motor plus energy source is a minimum. The key 

electrical consideration is total energy, not power. 

We will define the optimum design as the one which minimizes total system 

weight. After solving for the optimum motor weight we will than introduce the constraint on peak power and show that this limitation causes a shift from the minimum 

weight design. 

The volt-ampere load the torquer presents to the power supply is computed as 

follows: 

V = I R + KB w (1) 

I = T / KT (2) 

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P= VI =I (IR+KB w) 

-12R + KB I cs) 

, RKB4OT 

17-5 

armature loss mechanical work done 

on load 

watts (3A) 

Where: 

V = 

I = 

KB 

R = 

KT = 

T = 

co = 

P = 

terminal voltage, volts 

current, amperes 

back voltage constant, volts/rad/sec 

armature resistance, OHMS 

torque constant, ft-lb/amp 

load torque, ft. -lbs 

load speed, rad/sec 

power in watts drawn from energy source 

The ratio KB/KT may be shown to have the value 746/550 equal to 1. 36, 

which represents a conversion factor from English mechanical units of power 

(Ft-lb/sec) to 'watts. 

Using this constant, and substituting I from equation (2), equation (3A) may 

be expressed in alternate form: 

P = ( T)2 R 

KT 

+ 1. 36 Tw (3B) 

The second term in equation (3B) represents the mechanical power transferred 

to the load by electromagnetic induction. This term may be minimized by 

keeping both T and w small. This implies low torque and low speed. These 

parameters are functions of the mechanical design and the equipment operation 

profile. Torque has components due to friction and acceleration. The friction 

component will be minimized by using very 

T-- 3.S- 2..o SFICiAL 
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SPECIAL HANDLING -SECREThigh quality bearings. Acceleration and speed are contractor imposed requirements 

over which Itek has no control. 

It should be pointed out that in this application the torquers will be operated 

at very low speeds so that the I2

R loss term (due to contractor imposed acceleration 

torque) far exceeds the mechanical load power term. Since the second term is 

negligible compared with the first, we will concentrate our efforts on minimizing 

the loss term. 

The loss term represents heating due to resistance of the copper windings. 

It is possible to minimize such losses by using an oversize motor with smaller R. 

The question now arises: Will the extra weight of the oversize motor he offset by 

a greater reduction in the energizing system's weight? Note again that the discussion 

that follows is concerned only with minimizing the Ilk term in either of equations 

(3). We seek to minimize the weight induced by the loss term by an optimum tradeoff of motor weight and energizing system weight. 

Referring to (3B), the loss term is shown to be related to the torque T, the 

torque constant KT, and armature resistance R. 

A good design would be to choose a motor with large KT and small R,at the 

same time keeping T to a minimum. 

Although the torque loading is not a motor design parameter as such, it is auite 

apparent that any steps taken to minimize T will be well rewarded since the power 

loss is proportional to T2. We might briefly consider how operating time to, and 

power loss zre related. 

A frequent problem is choosing a torque or speed profile required to move a 

member some angle 14o 

in time t

o

. Notice that peak power is related to torque (T)

2

. 

It is observed that one should keep the peak torque substantially constant to 

maximize its second integral, which is position, and to avoid excessively high 

SPECIAL HANDLING -fit 

3.5- 1.1 
Ho/2 to 

t 

40. to 

F 1 G 1 

t

o/2 t 

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peak powers associated with tapered or contoured torque profiles, which contribute 

negligible integrated position. Accordingly, the profile selected will be one that 

provides constant rates of acceleration and deceleration. Such a profile is 

b) speed 9 

c) position 

T 

Using the well-known formula of mechanics, 0 = 1/2 a t

2 , we have: 

e 1 

a 

[ toil

2 4 0

o 

2 

• 

2 2 a 

t

o

2 

Since T = Ta, we have: 

T = 4

jo 

t,2 

Substituting-(5) into (3 B), we have: 

T N 2 P R + 1.36 TW 

KT 

4j0 

- [ 2

o 

KTJ

2 R + 1.36 TW 

t

o 

- R

2 + 1.36 TW 

to

4 KT

2 

(4j00)

2 

Power is therefore related to (l/t

o

)

4

. The fourth power behavior of power vs. 

t

o

calls for obvious use of t

o 

as long as is possible. The penalty of high accelerations is immediately made obvious. 

We now examine the factors R and KT, those motor parameters which we seek to 

optimize. 

SPECIAL HANDLING 

illustrated in Figure 1: 

a) torque 

torque )(A 

(4) 

(5) 

(6) 

3. j L 
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RELEASE 1 JULY 2015 SPECIAL HANDL= -G.EC-RETThe torque in a brushless torque motor is given by the equation: 

T = B IlnrK1 (7) 

Where: 

B = field strength, Gauss 

I = Armature current, amperes 

1 = length of conductor (in field B), meters 

n = Number of stator turns 

r = radius of armature, meters 

K

1 

= Geometrical form factor and proportionality constant 

Equation (7) places in evidence the conflicting factors that must be compromised 

in order to secure an acceptable design for a given application. 

A high field strength B is very desirable. This will be achieved by using a premium grade magnetic material. In order to achieve high torque sensitivity KT 

(torque/ampere) it is desirable that 1, n, and r all be large. Large r and 1 implies 

a thick motor with large radius, but this means a high weight. Large n and 1 implies a long winding length, and hence large ohmic resistance R. Making available 

more winding area (1 and r ) will permit use of a larger wire size, with attendant 

lower resistance, at the expense of more weight. K1 accounts for such non-linearities 

as leakage flux and air gaps. In general, large dimensions will tend to increase 

K1, again at the expense of weight. 

It is thusly apparent that a design of torque motor with arbitrarily high torque/ 

current and with arbitrairly low power loss for a fixed weight (itself arbirtarily low) 

is impossible. 

Having examined the factors which effect power consumption, we now consider 

the weight - power trade-off. We seek to minimize total system weight of motor plus 

energizer subject to a maximum power constraint. 

SPECIAL HANDLING SECRET 
W 

A t 

total 

+ We 

A 

motor energizer 

(8 ) 

d Wt = 1 + (d P (Wm)/dWm) (Hours) F 

d Wm 

; d Wt 

a wm 

= 0 for an extremum. (11) 

K2 

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SPECIAL HANDLING -SteRET--- 

The total system weight is given by the following equation: 

The term We 

may be estimated as follows: 

P(Wm) = motor input power as a function of weight that is required 

to develop load torque 

P (W ) (Hours) = watt-hours delivered from energizer through control 

m amplifier of efficiency n 

n 

P (W ) (Hours)F m = energizer weight in pounds (9) 

n K2 

Where: 

F = gimbal factor which is a measure of torque sensitivity decrease at wide 

angles 

Hours = total operating time in hours 

K

2 = energizer factor, Watt hours per pound 

(Typically 80 watt hours/lb for a silver-zinc battery and 1000 

watt-hours/lb of fuel for a 112 - 02 fuel cell) 

Equations (8) and (9) are combined to obtain: 

P (Wm) (Hours)F (10) 

n 

K2 

If P (Wm) was known in closed mathematical form, we could evaluate the 

following derivative to obtain the most favorable operating point: 

We 

Wt Wm + 

Previous discussion has pointed out that there are strong geometrical relationships between power and weight at a given torque level amoung output torque and 

motor geometry. Accordingly, a closed relationship P (Wm) does not seem unreasonable. 

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The following manufacturer's data was used to emperically derive a relationship 

between P(Wm) and Wm: 

AEROFLEX BRUSHLESS TORQUERS 

Model Weight 

(pounds) 

Peak Torque Power at 

Peak Torque 

Power at 

40 oz.-in 

Diameter 

Thickness ratio 

TQ 34 W 1.0 40 oz. -in. 20 watts 20 watts 3.38/.73 

(4.5/1) 

TQ 52 W 5.0 220 oz. - in. 80 2.6 5.1/1.5 

(3.4/1) 

TQ 82 W 11.3 480 oz. -in. 90 .62 8.19/1.40 

(5.2/11) 

INLAND BRUSH TYPE MOTORS 

Model Weight Peak Torque Power at Power at Diameter 

Peak Torque 1 ft.-lb. Thickness ratio 

T 3203 1.13 1.0 ft. -lb. 100 watts 110 watts 3.24/1.09 

T 4036 3.0 1.8 ft. -lb. 91 28 (3/1) 

3.9/1.25 

T 5135 8.5 4.0 ft -lb. 119 7.4 (3.1/1) 

5.1/1.5 

T 7202 11.5 11.0 ft -lb. 375 3.1 (3.4/1) 

7.2/1.6 

(4.4/1) 

Note that all of the above motors are of "pancake" construction, with approximately 

the same diameter thickness ratio. 

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Plotting the Aeroflex and Inland data on log-log paper (Figure 2 ) shows that 

the following function is a reasonable description of the relationship between 

weight and power: 

P = Po 

a 

(12) 

where a ranges from about 1.3 to 1.7. A value of 1.5 is a reasonable 

slope for fitting the plotted data. Accordingly, we have 

20 Aeroflex P (W

m

) = 

watts (13A) 

W1.5 

Inland P(Wm) 133 (13B) 

W

1.5 

The validity of equation (12) was confirmed in discussions with Aeroflex. 

Equations (13 A) + (13 B) relate the motor power required to develop 40 in.-oz. in 

the Aeroflex line and 1.0 ft.-lb. in the Inland Line as a function of motor frame 

size or weight. The selected motors of each vendor all have comparable thickness 

to diameter ratios: i.e., they are the same approximate form factor. 

In summary, use of equation(11) with a P (Wm) of equation (12) permits 

sizing of torquers so that the total weight of motor and energy source can he 

minimized. The constants 20 and 133 will change as (T/40)2, depending on the motor, 

where T is the new load torque. 

The Globe line of small DC brush torque motors was also examined for behavior 

as to watts vs. frame size at fixed torque. The power losses tended to remain fixed as 

the frame size went up, thus indicating that the increased copper, and hence reduced 

copper losses, were offset by higher brush friction, windage, and other losses. 

A previous report (document BOS-COR-9300-67-080 dated 16 March, 1967) 

estimated that a 9.4 hour total operating time was realistic. Let us examine the 

weight-power trade-off on this basis. The latest value of roll torque is 104 oz.- 

in./winding (total of 208 oz.-in.) and 13 oz.-in. per winding (26 oz.-in. total) 

on the pitch axis. The gimbal factors of 1.1 for pitch and 1.4 for roll of the referenced memo are assumed to apply.1--L-_CliAL HANDLING -5-E-C—K4— a.s-LL 
.410.0 

a \* T5135 

T9520 

'02 7 

982W 

• 

N 

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FIGURE 2 

Graphical Determination of Power vs. 

Weight Law for Two Types of DC Torquers 

100.0 ,11 T3203 

Inland 

T4U36 

both lines are 

a 

* T934W 1/113/2 approximations 

Aetoflex 

1.0 

0.1 

1.0 10.0 100.0 

Weight (lbs.) 

Si-LCIAL HANDLING SECRET 

3.S-27 
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The total weight of each axis 's motor is computed from equation (10) 

repeated below: 

Wt= Wm 

+ P(Wm) (Hours) (F) 

K2 

Each winding of one half the rated torque is assumed to act independently; 

the power and weight value/axis is double that of a single winding. This last 

equation (10) may be rewritten as: 

W

t 

= 2Wm PO K3 2 (14) 

where: 

K

3 

 = (Hours) (F) 

n K2 

F pitch = 1.1; F roll = 1.4 n = 0.8 (estimated) 

K2 , the incremental fuel energy constant in watt hours/lb. is estimated as 

1 Kw-hr. /lb for the oxygen-hydrogen fuel cell. Using this data, we have: 

K3pitch = 

(1.1) (9. 4) 

= 1.29 x 10-2 

(.8) (103) 

K3 roll (1.4) (9.4) = 1. 64 x 10-2 

(.8) (10 6) 

The Aeroflex motor constants PO 

P ( Wm ) 

Wrn 

1.5 

are computed as: 

Using a 5 lb. TQ-52 at 104 oz. -in., the power is computed as 80 (104/220) 

or 18 watts. Accordingly, 

18 = PO P

o 

= (18) ( 5)2/3 = 200 (15A) 

Using a 1. 0 lb. TQ-34&t 13 oz. -in, the power is computed as (13/40)2 

(20) 

or 2.2 watts. 

2. 2 = PO 

13/Z PO 2. 2 

3.5'23" 

(10) 

Wm 

2 

(15B) 
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The general form of (14) may be differentiated with respect to Wm; this 

yields: 

dWt = 2 + 2 Po K3 (3/2) Wm-5/2 (16) 

dwn 

Setting the derivative equal to zero to find the extremum, we have: 

Wm= [3/2 PoK3) 2 / 5 (17) 

Using previously computed values of Poand K3 of the roll and pitch axes, 

we have: 

2/5 

W

m 

Pitch = [(1.5) (1.64) 10-2 (2) 102

] 

= [4.9] 2/5 = 1.87 lbs. 

W

m 

pitch = [(1.5) (1.29) 10-2 (2.2)1 2/5 

= [4.3 x 10-2] 2/5 = 0.27 lbs. 

The total system weights then become: 

W

t 

= 2W

m 

+ 2PoK3 

W 3/2 

m 

For Pitch 

W = (2) (0.27) + ( (2) (1.29) 10-2 

t (0.27) 3/2 

= (0.54) + .41 = .95 lbs. 

For Roll 

Wt = (2) (1.87) + (2) (200) (1.64) 10-2 

(1.87) 3/2 

= 3.74 + 2.56 = 6.30 lbs. 

We now consider the peak powers that would be drawn: 

P = 2Po 

W

3/2 

For Pitch 

P 

x. (2.2) (2)= 31.5 watts 

(.27) 3/2 

SP LC i• ,1 

3. 5-- 2.1 

(14) 

L,. 
W

t = 2 W

m 

+ 2 KP b 3

W

m

3/2 

(2) (1.64) (200) 10

-2 

= (2) (5) + 5 3/2 

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For Roll 

P max - (2) (200) 

(1.87) 3/ 2 

= 155 watts 

These values are clearly above the subsystem power budget of 105 watts. 

Since no energy storage is available, the motor weights must be increased above 

the optium to restrict power. Just how to do this is a matter of engineering 

judgement. Consideration of other sub system power consuming elements 

dictate that about 40 watts of power be allocated for roll and about 4 watts be 

allocated for pitch. This decision makes use of motors near Aeroflex 

catalogue sizes, namely a double model TQ-34 for pitch and a single, somewhat 

reduced model TQ82W for roll. 

Using these motors, we have: 

LP pitch = 2 P

o 

(2) (2.2) 

3/2 3/2 (1.0) 

P roll = (2) (200) 

(5) 3/2 3 

The total system weights become: 

For Pitch: 

W

t 2Wm + 2 P

o 

K

3 

3/2 W

m 

= 4.4 watts 

= 36 watts 

= (2) (1) 1_ (2) (2.2) (1.29) (10-2) 

1 3/2 

2 + .06 = 2.06 lbs. 

For Roll: 

= 10 + 0.59 = 10.59 lbs. 

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The analysis may be summarized as follows: 

OPTIMUM DESIGN 

(Minimum system weight of motors plus energizer - no peak power restriction) 

Motor Weight Fuel Weight Total Weight Peak Power 

Pitch Axis 0.54 0.41 0.95 31.5 

Roll Axis 3.74 2.56 6.30 155.0 

4.28 2.97 7.25 186.5 

CONSTRAINED DESIGN 

(Subsystem power limited to approximately 40.4 watts for roll and pitch 

actuations) 

Motor Weight Fuel Weight Total Weight Peak Power 

Pitch Axis 2.0 0.06 2.06 4.4 

Roll Axis 10.0 0.59 10.59 36.0 

12.0 0.65 12.65 40.4 

The effect of the peak power limitation is to increase the weight of the 

sub-systems motors from the minimum of 4.28 lbs to 12.0 lbs. At the same 

time, the fuel load (elsewhere in the system) drops from 2.97 lbs. to 

0.65 lbs. The net system effect is a motor weight increase of 7.72 lbs., 

which is partially offset by a fuel savings of 2.32 lbs. The net system 

weight penalty caused by the peak power restriction is 5.40 lbs. (7.72-2.32). 

We conclude as follows: 

Although fuel weight is not an Itek responsibility, it is shown that 

minimum system weight (which is assumed to be a mutual objective) can only be 

realized when the gimbal motors are considered together with their energy 

source. Since the peak powers associated with the minimum weight design 

are prohibitive, the subsystem motor selection must be shifted away from the 

optimum point. There are no clear cut design procedures for locating the 

best constrained optimum. Engineering judgement, rather than mathematical 

3.5- 31 hANbL1- \io-' SECi2LI 
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HANDLF,', 3 SECRET 

formulation, must be used to allocate weight and power of individual 

mechanisms so as to stay within allowable subsystem budgets. 

Having determined that a total of 40 watts power can be allocated 

for slewing the gimbals, the design study results can be used to some 

extent to guide the motor design for minimum weight. To this end, Itek 

is specifying motor with premium magnetic components (high B), and investigating optimum motor geometries to obtain maximum torque with minimum 

weight and power consumption. These investigations will proceed until 

further returns are no longer obtained. 

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SPECr,I HANDL: ,:G ""ife.14E-T3.5.4 Miscellaneous Analysis 

This section contains several supporting analytical studies of general 

nature. They are principally products of the System Engineering effort. 

SECRET 

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SFECa 12ii1^N't 1 ' -SEC-RET3.5.4.1 Line-of-Sight and Gimbal Angles 

3.5.4.1.1 Scope 

This memo supercedes the two referenced memos which may be discarded since 

the appropriate information has been repeated here for completeness. 

Presented herein are derivations for line-of-sight (LOS) and gimbal angles 

for orthogonal pitch and roll axes with a cant rotation about the third 

orthogonal axis (vehicle z-axis). Results of computer solutions to these 

expressions are given for several angular positions and worst case 

conditions. 

3.5.4.1.2 Derivation of LOS Angles 

The line of sight with respect to vehicle reference is formed by taking the 

unit line of sight vector and applying the pitch, roll and cant rotations. 

Thus: 

L

v 

• L R Rrt R

c 

where: L • [0 0 11 

R = Cos pt 0 -Sin pt 

Pt 

0 1 0 ; pR • LOS pitch angle 

Sin pi 0 Cos pt 

FifIi;bLit-4C; 3.5-31( 
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I.- a -T 

R

rt = 1 0 0 

0 Cos ri Sin ri ; ri = LOS roll angle 

0 -Sin ri Cos ri 

R

c 

= Sin c 

••■•■•111. 

Cos c 0 

-Sin c Cos c 0 c = gimbal cant angle 

0 0 1 

This gives: 

L

v 

= + 

- 

L

x 

L 

y 

L

z 

(1) 

Sin pt Cos c 

Sin pi Sin c 

Cos pi Cos ri 

Cos pi Sin rk Sin c 

Cos pi Sin VI, Cos c 

Now define the two pointing angles with respect to vehicle coordinates as: 

a .0 roll angle measured in y-z plane. 

= pitch angle measured in x-z plane. 

Then: 

-L Tan a - Tan a - Lx 

L L 

z z 

Now, solving for LOS angles: 

Tan ri - Tan 0 Sin c + Tan a Cos c 

Tan pi Tan a Cos 11 - Sin ri Sin c -Tan a Cos ri + Sin ri Cos c = 

Cos c Sin c 
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r's cc, ra 

3.5.4.1.3 Derivation, of Gimbal Analog 

Since the optical path between the moving and fixed mirrors is always parallel 

to the vehicle x-axis and the line-of-sight from the moving mirror is known 

from the derivation above, the normal to the moving mirror can now be found. 

A 

Lv+ X 

■

I L i 

n

x 

n / 

y / 

n

z 

(4) 

Now, referring to Figure 1 and doing a bit of trigonometry the gimbal angles 

are: 

Tan rg a On sec c + (n

x 

- n tan c) sin c) / n

z 

(5) 

Tan pg - (n

x 

- n tan c) cos c cos rg / n y 

z 

(6) 

It is possible to arrive at a more fundamental form of equations (5) and (6) 

by use of equations (1) and (4). However, there is little computational 

difference, so equations 2, 3, 5, and 6 were used in computer program PLUM 

to calculate the LOS and gimbal angles. A copy of PLUM is attached for 

those interested. 

3.5.4.1.4 Results 

The results of this study are given on individual data sheets attached. Each 

sheet gives either the LOS or gimbal angles for a given cant angle. The top 

chart shows the extreme or worst case angles along with the corresponding LOS 

angles with respect to vehicle axes. This gives the pitch and roll ranges 

required to cover the entire +70° to -40° in pitch and +45° in roll. The 

lower chart shows the angles corresponding to various points of interest within 

the total range. For example, no vignetting is allowed between +10° and +40° 

in pitch. Data for any other angles is available on request. 

SPECIAL HANDLING SECRET 

3.1- 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Sr "It L HANDLING S 

31/32/3300 FORTRAN (2.1)/MSOS 03/30/67 

PROGRAM PLUM 

C 

C PLOT NO ANGLES 

C K NEW SAME PLOT LOS GIM 

C 1 X Y. 

C 2 X X 

C ) X X 

C 4 X X 

C 5 X X 

C 6 X X 

C 

KIDL=49 

C 

RPD=0.0174532425 

DPR=1.0/RPD 

C 

100 REAU(60,1001) AMIN,AINC,AMAX,SMiN,BINC,BMAX,CD,K 

GO I0(101,102,101,1U2,101,102) K 

101 WRITE(61,1003) CD 

GU 10 103 

102 WRITE(61,1004) CD 

103 IF(AMIN.EQ.200.11) 800,104 

104 GU TO(110,110,11_15,105,110) K 

105 CONTINUE 

IF(AXISXY(KPLA1U,11,10.0/26.0,10.0,11.0.0,1.0,0.0,0.0,10.0/26.0 

$,2)) 106,900 

106 CONTINUE 

CALL rLOTXY(0.1.-0.9,0,0) 

CALL PLOTID(0) 

110 CW=CD*RPD 

SINC=SIN(CP) 

COSG=COS(k;R) 

IMIJ=AMIN 

IING=AINC 

IMAX=AMAX-AMIN+1.0 

DO 300 1=1,IMAX,IINC 

AD=I+IMIN-1 

AR=AU*HPD 

FANA=TANF(AR) 

JMIN=BMIN 

JINC=BINC 

JMAX=BMAX-8MIN+1.0 

DO 280 J=1.JMAX,JINC 

BIJ=J+JMIN-1 

BR=d00,RPO 

TAN8=TANF(HR) 

RR=ATANF(TANA*COSC+TANB*SINC) 

PR=ATANFUTANB*COS(RR)...SINC*SIN(RR))/COSC) 

GU T0(120,122,120,122,120,122) K 

120 SINP=SIN(PR) 

COSP=COS(PR) 

SINR=SIN(RR) 

COSR=COS(RR) 

ENX=SINP*COSC+COSP*SINR*SINC+1.0 

3. s —31 - tGihL ii-tm.A..ING SECRET 
-TIRO APPROVED FOR 

RELEASE 1 JULY 2015 

SPECIAL HANDLING 

ENY=-SINP*SINC+COSP*SINM*COSC 

ENZ=COSR*C(MR 

OEN=SQRT(ENX*ENX+ENY*ENY+ENZ*EN2) 

ENXN=ENX/OEN 

ENYN=ENY/OEN 

ENZN=ENZ/OEN 

FACT=ENXN-ENYN*SINC/COSC 

RR=ATANF((ENYN/COSC+FACritSINC)/ENZN) 

COSR=COS(RR) 

RR=ATAN1:((FACT*COSC*COSR)/ENZN) 

122 RD=RR*DPR 

PO=PR*DPR 

WRITE(61,1002) CD,AD,8O,RO,R0 

GO T0(280,280,130) K 

130 X=(RO+50,0)/12.0 

Y=('0+50.0)/16 .0 

CALL PLOTXY(X,Y,0,11) 

280 CONTINUE 

300 CONTINUE 

GO TO 100 

800 CONTINUE 

GO 10(900,900,850) K 

850 CALL AXISXY(0,0,0,0.0,0.0,0.0,0.0,0,0,0.0,0.0) 

900 RETURN 

C 

1001 FuRmAT(/F10.0,12) 

1002 FuRmAT(5x,5F10.2) 

1003 FOPMAT(1H1,3mGIM,5X,3FICD=,F4.1,46X,1HI) 

1004 FORilAT(1H1,31-1LOS,5X,3HCO=,F4.1,46X,1HI) 

- C 

END 

3200 FORTRAN DIAGNOSTIC RESULTS - I-- OR PLUM 

NO ERRORS 

LOAD,56 

RUN 

SPECIAL HANDLING SECRET 
T13, 

in n, A-o.nc\ %111 c 

• x 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SFEC;:i 1- ANDL"' 

Figure 1 

. • 

1.s - 39 
- NRO APPROVED FOR 

RELEASE 1 JULY 2015 

LCIAL F:ANDLING SCCRCT 

LOS 0 „ 

Angles for Cant 

3/28/67 

Geometry I 

Entrees Amass 

Corresponding LOS hellos 

(with reepeet to sehiele azes) 

Roll Pitch Roll 

. -... 

Pitch 

-45.00 -45 any 

-40.00 0 -40 

+70.00 0 +70 

+45.00 +45 any 

+62.76 

8 

0 ...? + 

+70.00 

0 

+1 

+62.76 

0 0 

- LA ...t I 

+30.68 

8 

0 ..1. + 

+40.00 

0 

+1 

+30.68 

0 0 

in 

a I 

-V; 1--, 

+45.00 ' 

+10.00 

0 

+I 

+7.11 

0 0 

tri ...i. 1 

1+ 

O 

+45.00 

- + 0 

0 

+I 

+ 0 

0 0 

v+ ..r1 

w 

o Os 

+45.00 m 

-40.00 

0 

+I 

-30.68 

0 

0 ri 

in 

r 

.4. 

+70 

+40 

PITCH 

(LOS analog 

with respect 

to vehicle 

axes) +10 

0 

-40 

0 

• 

a .12 

ii4" 

.St 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 3/28/67 

LOS Angle. for +5 Cant 

Geometry I 

Extreme Angles 

Corresponding LOS Angles 

(with respect to vehicle axes) 

, . 

Roll 

, 

Pitch Roll 

. -. 

Pitch 

-46.92 -45 -40 

-40.26 +10 -40 

+70.08 -15 +70 

+51.02 +45 +70 

+59.04 

N 

0 

11-. in 

+ 

+69.41 

r, 

-4 

M 

,...1 

+ 

+66.06 

N 

ri 

r--. m 

I 

+27.09 

N 

M 

,i; 

..7 

+ 

+39.82 

m 

1-1 

,I 

+ 

+34.15 

r-1 

r-. 

N 

,1' 1 

+45.33 • 

rn

+9.96 

co 

co 

c; 

+ 

+10.63 

in 

-4- 

-4- 

+44.89 • 

+ _ 0 

o 

+I 

+3.53 

rn 

m 

-4.- ...t 

I 

+42.71 

-39.82 

co 

v-i 

I 

-27.09 

N 

M 

....7 

+70 

+40 

PITCH 

(LOS angles 

with respect 

to vehicle 

axes) +10 

0 

—40 

O 

• 4-s-, 

a'S j r.27O4 

3, 5 "if :DUNG SECRE 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

'1r4r_PI A I 1N3LAC 

3/31/67 

Angles for +6 Cant 

Geometry I 

Entree* Angles 4 

Corresponding LOS Angles 

(with respect to vehicle axes) 

p 

Roll Pitch Roll 4 

• 

_ Pitch 

-47.26 -45 -40 

-40.37 +12 -40 

+70.11 -18 +70 

+52.04 

.. 

+45 +70 

_ 

LOS 

+58.26 

O 

(NJ Ill 

+ 

+69.15 

o 

4:. r-i 

+ 

+66.65 

c.) 

tti ("I I 

+26.35 

q:. 

Cs1 

. N. 

+ 

+39.74 

1.4 

0 

+ 

+34.82 . 

0 

C,1 

c•, 

I 

co 

+45.37 Li' 

+9.94 

ko 0 

.-1 

+ 

+11.33 

.--1 

cn 

4 ...? I 

-4.24 

...4- 

co 

4 -4- 

+ 

+ 0 _ 

. o 

+1 

+4.24 

....t Co 

4 ...t 

lJ 

+42.20 res,' 

-39.74 

r-4 

• 0 

vi 1 

-26.35 

V::. 

Cs3 

r-. ...? 

0 

.4 

I. I 

r 

+70 

+40 

PITCH 

(LOS angles 

with respect 

to vehicle 

sass) +10 

0 

-40 

■1- ;Ai ,■ 1.)1.1i 4G 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3/31/67 

SPECIAL I-I,ANDLING 

Assisi for +7 • Cant 

Geometry I 

Extreme Aisles 

Correspondiss LOS Miles 

(with respect to vehicle axes) 

Roll Pitch Roll Pitch 

-47.59 

+53.01 

-40.51 

+70.16 

-45 -40 

+14 -40 

-21 +70 

+45 +70 

LOS 

+57.46 

,-1 

o 

cri Ln 

4- 

+68.86 

.-4 in _ 

c6 ri 

+ 

+67.21 

m 

M M i 

+25.62 

n. -1. 

+ 

in in 

+39.64 

...t 

co 

it; 

+ 

+35.49 

co ‘.4o 

. i-il 

...t 

1 

N.) 

+45.40 

+9.92 

m 

cs, 

.4 

+ 

+12.02 

.0 ,-1 

....? 

.., I 

-4.94 

on 

rs.. 

i 

+ 0 

o 

+ I ' 

+4.94 

cr, 

N. 

...a 

4. 

I 

-35.49 

co ‘o 

..1 

+ 

_ 

-39.64 

4. co 

it; 

I 

-25.62 

cr. in 

4- I 

1 0 

+70 

+40 

PITCH 

(LOS eagles 

with respect 

to vehicle 

axes) +10 

0 

-40 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

'n"^LL- SECRET 3/28/67 

LOS Angles for +8 • Cant 

Geometry I 

. 

Extreme Angles 

Corresponding LOS Angles 

(with respect to vehicle axes) 

Roll Pitch Roll , 

Pitch 

- 

-47.91 -45 -40 

-40.66 +16 -40 

+70.20 -24 +70 

+53.93 +45 +70 

+56.66 

m 

a+ 

m 

tn 

+ 

+68.52 

m a+ 

c..; 

Cs! 

+ 

+67.75 

o 

m 

.4 

en 

I 

+24.88 

,-1 

m 

N. 

-4. 

+ 

+39.53 

,a gD 

s4; 

+ 

+36.15 

.4. ,--1 

,--i .4. 

t 

+1.42 

N 

, + 

.../. ..1- 

+9.90 

—1 

+ 

+12.72 

8 

1 

-5.65 

4,1 

r.. 

....; -4- 

+ 

- 

+ 0 

o 

+1 

N. 

+5.65 

CV 

4. 

It 

-36.15 

.4- ,-1 

4 

+ 

-39.53 

sz 

,.o 

.1.; 

-24.88 

.-1 

cs, 

r-- 

i 

a .'7 g4" gits1 

1/1'. fiCRET 

+70 

+40 

PITCH 

(LOS angles 

with respect 

to vehicle 

axes) +10 

0 

-40 

3.5 - 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 3/31/67 

-4..-: Eertell 

LOS Angles for +9' Cant 

Geometry I 

Extreme Angles 

Corresponding LOS Angles 

(with respect to vehicle axes) 

, . 

Roll 

, 

Pitch Roll 

. 

Pitch 

—48.21 —45 —40 

—40.83 +18 —40 

+70.26 —26 +70 

+54.80 +45 +70 

+55.85 

o 

m 

.4 in 

+ 

+68.14 

,o N 

m 

N 

+ 

I +68.25 

s.o --1 

c..4 

N 1 

+24.13 

,-1 

N 

m 

...t + 

+39.41 

co 

..., . 

7 

4- 

+36.81 

co 

in 

. O

.0. 

1 

! +13.41 

m 

co 

m 

+

1 

45. 43 

+9.88 

m in 

+ 

—6.35 

.1 

so 

.1- -st 

+ 

—36.81 

co u.) 

O 

4- 

+ 

+ 0 I 

I 

0 

+1 

—39.41 

co .4. 

I-, 1 

+6.35 

m 

so 

...1- -.1- 

1 

—24.13 

,--1 

c., 

cc; -...+ I 

+70 

+40 

PITCH 

(LOS angles 

with respect 

to vehicle 

axes) +10 

0 

—40 

0 in 4. 1 

1 

g14.VI 

I• VI 1.1 ' • 

3. s'—'15— V E 2 11„ _ 

,,o,... DUN :., ',41kir 
--NRO APPROVED FOR 

RELEASE 1 JULY 2015 

LOS 

-4 z a ±etr. L. • Angles for _to_ 3/28/67 

Geometry I 

Marone Angles 

Corresponding LOS Angles 

(with respect to vehicle axes) 

Roll Pitch Roll Pitch 

-48.51 

+55.63 

-41.03 

+70.32 

-45 

+20 

-29 

+45 

-40 

-40 

+70 

+70 

+55.03 

01 

%0 

in 

+ 

+67.73 

,•1 in 

LA 

N 

+ 

+68.72 

CV 

M 

L.c.) 

N 

1 

+23.39 

ul 

c; 

+ 

.4 . 

+39.27 

m 

cs, 

0; 

+ 

+37.45 

o 

o 

8 -4- 1 

+0.00 

.4- 

...t 

-a 

+ 

+9.85 

Ln 

1--. 

+ 

+14.10 

4:, Lc 

cA 

....v 1 

-7.05 

,o 

....i. 

..1- 

+ 

+ 0 _ 

o 

id 

+7.05 

Lt. 

...1 

-.1' 

I 

-37.45 

o o 

8 ...+ + 

-39.27 

m 

N 

cc; I 

. , 

-23.39 

Lr, '-I 

m .4. ; ■ 

• a, 

0 • 

e s I 

+70 

+40 

PITCH 

(LOS angles 

with respect 

to vehicle 

axes) +10 

0 

-40 

. .1 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

:1!PECL,L HANDLING • 

Gimbal Angles for 

3/28/67 

Geometry I 

Extreme eagle. 

Corresponding LOS haglike 

(with respect to vehicle axes) 

Roll Pitch loll Pitch 

-45.00 

+45.00 

+25.00 

+80.00 

-45 

0 

0 

+45 

any 

-40 

+70 

any 

+76.38 

o 0 

.,; 

.. + 

+80.00 

'7 

+76.38 

8 

. 

I 

+60.34 

0 0 

In 

+ 

+65.00 

'1 

+60.34 

o 

0 

n 4. 1 

+48.55 

0 

o 

+50.00 +48.55 

o 

o 

..r; 

+45.00 

o 0 

,,, 

.4 

+ 

+45.00 +45.00 

8 

u-; 

a 

I 

+29.66 

0 o 

+25.00 

it; in 

+29.66 

0 o 

+70 

+40 

PITCH 

(LOS angles 

vith respect 

to vehicle 

axes) +10 

0 

-40 

In 0 

gi iY a 

1 s - 
--NRO APPROVED FOR 

RELEASE 1 JULY 2015 

- ".`10 SECRET 

3/31/67 

Gimbal Angles for +5 • Cant 

Geometry 

Entrees Angles 

Corresponding LOS Angles 

(with respect to vehicle axes) 

r 

Roll 

• Pitch Roll Pitch 

—42.80 —45 —40 

+24.07 +19 —40 

+80.12 —29 +70 

+56.40 +45 +70 

+72.49 

) o ..1- 

,c) in 

+ 

+78.83 

o 

en 

,s; 

cs, 

+ 

+79.33 

a, 

a, 

In 

cs, 1 

+56.63 

cr, 

...t 

c; to 

+ 

+64.54 

a, In 

o 

■•••1 

+ 

+63.66 

in 

a, 

r-, 

C.") 

I 

+44.90 

...1- ,o 

co ...i. + 

+49.74 

el 

cy, 

..-; + 

+51.95 

co to 

0 .../. I 

+41.36 

m 

N 

00 

st 

+ 

s 

+44.78 

CO 

01 

.1• 

+ 

+48.42 

. " ■I 

14 

st 

I 

. 

+26.07 

--+ m 

,4; 

+ 

it 

+24.90 

m m 

+ 

_ 

+33.13 

o 

m 

. 

cs, 

I 

1 

+7 

+40 

PITCH 

(LOS angles 

with respect 

to vehicle 

axes) +10 

0 

—40 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

L-Cd NDLIN —11 3/31/67 

Gimbal Angles for 

Geometry I 

Extreme Angles 

Corresponding LOS Angles 

(with respect to vehicle axes) 

v 

Roll Pitch Roll Pitch 

-42.31 -45 -40 

+23.68 +22 -40 

+80.17 -34 +70 

+58.07 +45 +70 

+6 • Cant 

+71.65 

o 

0:3, L n 

+ 

+78.35 

.0 .0 

6 

cr, 

+ 

+79.73 

c., 

o 

-; 

(NI 1 

+55.86 

m 

v-7I 

Ul 

+ 

+64.34 

m 

s.0 

N 

rI 

+ 

+64.26 

-4 

M 

sr; 

M 

, I 

+44.15 

m 

N 

m 

+ 

+49.63 

0 ,-1 

+ 

+52.60 

m Lri 

m I 

+40.61 

0 

m 

cci 

+ 

+44.69 

. 

N O. 

+ 

+49.07 

in N 

c; 

1 

+25.33 

N -4 

N. 

+ 

-4- 

+24.85 

O. 

r-- 

+ 

N 

+33.80 

,-1 m 

N 

1 

O 

*It 

+70 

+40 

PITCH 

(LOS angles 

with respect 

to vehicle 

axes) +10 

0 

-40 

'41 

a . 

rr 

tANCLii,G 

I" 

SECRET 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SF-EC1AL HANDL:7 'T Stan" 

Gimbal Angles for ±L_' Cant 

3/31/67 

Geometry I 

Ixtress Angles 

Corresponding LOS Angles 

(with respect to vehicle we) 

Roll Pitch Roll Pitch 

-41.81 

+59.59 

+23.25 

+80.24 

-45 

+24 

-38 

-45 

-40 

-40 

+70 

+70 

+70.80 

m 

in 

cl; 

+ 

+77.81 

in %JD 

.4.- 

+ 

+80.04 

o N. 

Lt.; 

1 

+55.07 

in 

M 

cs, in 

+ 

+64.10 

in 

m 

...i. ,-1 

-I- 

+64.84 

o gD 

-.3. in 

I 

+43.39 

o 

m 

CI; 

-4' 

+ 

+49.49 

q:, 

N 

CO 

+ 

+53.23 

, in 

CO M 

I 

+39.86 

qp M 

M 

...1- 

+ 

+44.57 

V) 

M 

q; 

+ 

+49.71 

%ID 

M 

CT M 

I 

+24.60 

co 

..1- 

+ 

...1- 

+24.80 

in 

N 

in 

+ 

+34.47 

-. 

m 

-...t I 

O 

• 

3.,S - so 

+70 

+40 

PITCH 

(LOS angles 

with respect 

to vehicle 

axes) +10 

0 

-40 
O 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 3/31/67 

SFECIANDUNGefiffGimbal Angles for +8 Cant 

Geometry I 

Estrous Angles 

Corresponding LOS Angles 

(with respect to vehicle axes) 

, . 

Roll Pitch Roll Pitch 

-41.29 

+60.98 

+22.77 

+80.31 

-45 

+27 

-42 

+45 

-40 

-40 

+70 

+70 

+69.93 

m O. 

O 

NC7 

+ 

+77.22 

co 

cq 

0; 

0", 

+ 

+80.26 

co 

o 

c; 

r•-I 

I 

+54.28 

co ,.4 

cn ,r) 

+ 

+63.83 

N 

m 

%c) ,-1 

+ 

+65.40 

.-1 

co 

ev 

m 

I 

+42.62 

o ,r) 

o ul 

+ 

_ - 

+39.10 

m 

m 

a, .4- 

+ 

+49.34 

c., 

...7 

m 

+ 

+53.84 

 tr, o 

r--. 

m 

I 

+44.45 

cv 

m 

r-.. 

+ 

+24.74 

--I N. 

C', 

+ 

+50.34 

m -.1 

co m 1 

+23.86 

m (-... 

.../. 

+ 

t 

+35.14 

m 

cq 

-7 I 

+70 

+40 

PITCH 

(LOS angles 

with respect 

to vehicle 

axes) +10 

0 

-40 

Y

h 
g ltill girel 

rCirl 

a4, 

FPFrir' 

— NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3/31/67 OLING tteRET-- . 

Gimbal Angles for +9 • Cant 

Geometry I 

Extreme Angles 

Corresponding LOS Angles 

(with respect to vehicle axes) 

, • . 

Roll Pitch Roll Pitch 

-40.75 -45 -40 

+22.25 +29 -40 

+80.39 -45 +70 

+62.25 +45 +70 

+69.05 

to cv 

. 

N 

+ 

+76.58 

co .n 

....1 

+ 

+80.39 

%et 

es., 

Nil I 

+53.47 

o cD 

. 

-.4. in 

+ 

+63.53 

in 

in 

+ 

+65.93 

cn 

a, 

c; ri I 

+41.85 

co 

o 

. 

.-1 

in 

+ 

+49.17 

'.0 

u-, 

c:3 .-1 

+ 

+54.45 

0 .../. 

cn I 

+38.33 

o .I. 

Li.) 

+ 

cir.... 

+44.30 

cl, 

CC; 

+ 

co 

+50.95 

r, 

....? 

(VI I 

+23.12 

co 

cc; -4- 

+ 

o r.. 

÷ 24.67 

.-1 

. -4 

+ 

+35.79 

in 

r... 

c; 

.4. I 

el) 

+70 

+40 

PITCH 

(LOS angles 

with respect 

to vehicle 

axes) +10 

0 

-40 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3/31/67 

SPEC,i,AL HANDLING SECRET 

Gimbal Angles for tie Cast 

Geometry I 

Extreme Angles 

Corresponding LOS Angles 

(with respect to vehicle axes) 

Roll Pitch 

. 

Roll Pitch 

-40.20 

'• 

-45 -40 

+21.69 +31 -40 

+80.41 -45 +70 , 

+63.42 +45 +70 

, - 

+68.16 

N .4- 

M ,47) 

+ 

+75.89 

so ,r) 

i 

I 

+80.41 

s.rz 

+ 

----, 

+52.66 

N. 

r■ 

• 

.4 tr) 

+ 

+63.19 

N 

■1- 

C; . 

N 

+ 

--4- 

+48.97 

cr. sa 

.-1 + 

+66.43 

T., 

ON 

M . ev I 

+41.06 

,c, 

in + 

+55.03 

,r, 

N 

en 

r 

+37.56 

o 

cr, 

O kr, 

+ 

+22.37 

,r., 

m 

op ■1* 

+ 

+44.14 

.s., m 

a; 

+ 

+24.59 

m 

■7 

+ 

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3.5.4.2 Sun Sensor 

3.5.4.2.1 Introduction 

The sun sensor will consist of a group of illumination sensors arranged 

to detect the image of the sun. in the sensor field of view. 

Two types of light sensors have been considered, photovoltaic and 

photoconductive. The photovoltaic does not need an external voltage source 

because it generates its own voltage as a function of the light intensity. 

The photoconductive sensor (photo transitor) needs an external power source 

to back bias the diode junction. The incident light intensity tends to cause 

forward bias, thus lowering the resistance of the device. The sensitivity 

of the photoconductive sensor is On the order of twice the sensitivity of the 

photovoltaic type. 

3.5.4.2.2 Design Description 

Considering the photo transistor as being similar in function to the 

more common types, a silicon unit seems appropriate in consideration of environmental conditions and contractor imposed requirement banning the use of 

germanium semiconductors. 

The silicon phototransistor is recommended because it can generate a 

large voltage variation at a low impedance level. The device impedance 

at 50 mw/cm2 is about 30011.. The disadvantage of phototransistor is the 

variation in gain from unit to unit. If a phototransistor is changed, 

the system has to be recalibrated. The phototransistor gain will also 

change with temperature, thus varying the threshold level of the sun sensor. 

I C 'Ji4 

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the ultimate output is of an on-off nature. Illumination on the detector 

surface of 20,000 ft.candles should cause the detector to activate the 

shutter. This is well within the safety factor for the brightness of 

the sun above the atmosphere which is approximately 130,000 ft. candles. 

Parameter variations that cause difficulty in a proportional design will 

be circumvented by proper signal processing. 

The two photoconductive devices chosen for study are the Texas 

Instrument LS-810 phototransistor and General Electric L14A502. 

Their characteristics are presented as follows: 

PHOTOTRANSISTOR CHARACTERISTICS 

LS-810 L14A502 

Power Dissipation 75 300 mw max. 

Reverse Voltage 30 45 V

dc 

Operating Temp. Range: -65°C to 125°C -65°C to 150°C 

Sensitivity 300 a/mw/cm2* 

300 a/mw/cm2** 

Measured with radiation of 9 mw/cm2 

 in wave lengths of .7 to 1.0 microns 

** 

Radiation source is an unfiltered tungsten filament bulb at 2870°K 

3.5.4.2.3 Conclusions 

Although the basic design of the sensors has been investigated the 

parameters such as sensor type (optical or non-optical), location, wiring, 

weight, field of view etc., must still be decided. Following trade-off 

discussions, the operating parameters will be crystalized and then an 

appropriate sensor chosen. The field of view will be dependent upon sensor 

location. 

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s • • ••■ 

h; • •-. 

BOS-COR-9300-67-089 

COPY NO. 

411111=1■0' 

To: R. Heath 

From: J. Galligan 

Subject: Slant Range Focus Shift 

DATE: 29 March 1967 

1.0 Introduction 

The telescope must operate over wide slant range excursions. These. 

changes in range result in a shift in the location of the objective lens 

focal plane. For the present optical design, the focal plane shifts as a 

function of roll and pitch angles are depicted in Figures 1 - 5. 

2.0 Method of Calculation 

2.1 Assumptions 

The defocus values in the figures are predicated on the following 

assumptions: 

a. The slant range was calculated for a flat earth. 

b. The pitch and roll angles are referenced to the vehicle; 

crab angle changes were not considered. 

c. The reference object distance for the infocus condition is the vertical 

altitude of the telescope. 

d. Any defocus due to power changing or zooming will add directly to 

the values in the curves. 

2.2 Slant Range Defocus 

The following equation was used to evaluate the magnitude of the slant 

range defocus errors: 

1. - 

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f 2 

AfSL 

= IT (1 - cos (1) cos 0) where 

AfSL slant range defocus error 

f = focal length 

h = altitude 

(1) = pitch angle 

0 = roll angle 

A derivation of this equation is in an appendix. Defocus errors were 

calculated for nadir altitudes of: 70, 80, 100, 150, and 230 nautical miles. 

The pitch angle variation is from 0° to 70° and the roll angle increments are 

0°, 20° and 45°. The curves are valid only if the system was focussed at 

nadir. If an object distance greater than nadir height is used, the values 

must be recalculated. 

3.0 Discussion of Results 

Taking the 80 n.mi. case as a typical example, the worst case slant 

range defocus is .0007 inches in the high power mode at the objective lens 

focal plane. At the eyepiece object plane this corresponds to approximately 

.003 inches. The low power mode worst case is negligible. Thus the separation 

between the reticle and the scene planes is approximately .003 inches in front 

of the eyepiece. 

The possible effects of such a displacement can be discussed qualitatively. First, the reticle may appear to lose some of its definition causing 

the observer's eye to have to refocus as he concentrates either on the 

reticle or the scene. This will not be a cause for concern in the present 

design since the eye has a depth of field of .5 diopters and the .003 inches 

separation corresponds to .13 diopters. In summary, at the present time, the 

3.s-S1 

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L_ LPage 3 

reticle/scene defocus should not be considered a problem area, but it should be 

further studied if the magnitude of the defocus becomes significantly greater 

due to other defocus causes. 

The second effect of the slant range focus shift is one of parallax. If 

the reticle and objective lens focal plane are coplanar, then the reticle can 

be used as an aid in aiming and tracking any part of the field. However, if 

reticle and focal plane are not coplanar, then the reticle could appear to be 

centered on a target at the edge of the field while in fact it is not. This 

could introduce aiming and tracking rate errors. At the highest power, the outer 

ring of the reticle subtends an angle of 15° in the eyepiece field. If the reticle 

and scene are separated by .0035 inches, as in the case below, the angular parallax 

will be approximately three arc-minutes. The acuity of the eye is sufficient to 

detect this angle. Figure 6 shows the relationship of the angle of parallax 

to the apparent semi-field angle at highest magnification out to the location of 

the outer ring of the reticle. 

In summary, a worst possible case will be discussed. If the system was 

focussed for an 80 n.mi. object distance and was then taken to a 230 n.mi. altitude and used on a target located at +70° pitch angle and +45° roll angle, the 

defocus would be .0008 inches at the objective focal plane. This corresponds 

to approximately .0035 inches at the eyepiece object plane. Therefore, the worst 

case for slant range defocus results in a .15 diopter shift which is well within 

the limit of the eye's depth of focus. 

Approved: 

A. Van Sickel 

Dist: F. Bean 

P. Clifford 

S. Robinson 

A. Van Sickel 

A. L. Wright 

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Page 4 

APPENDIX 

1. Slant Range: SR = h sec 0 sec 9 = h h 

(Flat Earth) 

(See Figure a) 

2. Image Distance for a nadir in-focus condition: 

S

h f 

N _ 

h - f 

3. Image distance for a slant range change: 

Sc _ (h + h) f 

(h f ph) - f 

4. Defocus; 

SN- Sc = Laf h f (h + 4 h) f 

h - f (h + A h) - f 

5. After algebraic manipulation: 

h h sec 0 sec 0 - f - 

(h -0 (h sec 0 sec0: 1(- hf-

) f) (sec 0 sec 43)3 

h (sec 0 sec 8 - 1) 

h l sec 0 sec -0 - f h (1 + sec 0 sec 9) + f 

6. Approximation: 

The last two terms in the denominator can be neglected since the worst 

case error that would be introduced is one part in seventy (1/70) or 

.0001%. 

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Therefore: • f 

f 2. 

(sec 0 sec 0 - 1) 

h sec 0 sec 0 

A f 1- cos 0 cos 0 

f 2 

• f = 

f

I 

I-1[1 - cos 0 cos 

7. The results were evaluated for this expression. 

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OBJECTIVES 

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• DETERMINE CREW STATIC VISUAL THRESHOLD CHARACTERISTIC 

• EVALUATE RESOLUTION DEGRADATION CAUSED BY SINGLE FREQUENCY 

SINUSOIDAL JITTER 

SECONDARY 

• EVALUATE THE EFFECT OF SCENE BRIGHTNESS ON RESOLUTION 

• DEVELOP A WEIGHTING FUNCTION FOR APPLICATION TO THE SERVO 

DESIGN AREA 

EXTENSIONS 

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3.5.4.4 Image Motion Experiment 

Since image motion will undoubtedly be introduced into the AO image plane 

by the scanner, a preliminary study of the effects of image motion on resolution 

was conducted. The results of this study and recommendations for further 

effort are stated in this section. 

A standard Air Force Tri-Bar target with a 2:1 contrast and illuminated 

by 180 foot-lamberts was mounted on a slide. This slide was then placed 

in a tray which was sinusoidally vibrated by a speaker cone. For various 

combinations of frequency (4,6,8,10,20 and 50 cycles per second) and amplitude 

(+ 0.25, + 0.5, + 1.0 and 2.5 arc-seconds, five observers recorded the maximum 

resolution they could perceive in the target. The results of this experiment 

are shown in Figure 3.5.4.4-1. 

The trends in the data shown in the figure are as follows: 

a. The 6-8 CPS region appears to be the place where the curve slope 

changes most abruptly, indicating a higher tolerance in motion 

amplitude for resolving the same target, for lower frequencies. 

b. One observation - for an individual who passed a physical examination 

for pilot training - indicated a higher amplitude tolerance in the 

8-10 CPS region. 

c. All observers, whose eyes were capable of resolving 3.5' equivalent GRD, 

managed to do so at motion amplitudes greater than 4- 0.25 arc 

seconds. 

The significance of the aforementioned trends is this if further experiments 

show that image motion does not degrade resolution as severely as was first 

postulated by sine wave response analysis, the scanner servo design criteria 

may be relaxed. Thus it is imperative to perform this experiment in a very rigorous 

manner, adhering to the design criteria for the AO as much as possible and 

varying the motion input (random, sinusoidal, and linear superimposed on a 

sinusoid) in order to determine the magnitude of the image motion effects. 

The preliminary investigation showed trends which were favorable to a 

relaxation of the scanner servo tolerances. Now further analysis must be done 

to reinforce this conclusion and to determine the magnitude of the effect. 

Only a limited amount of in- scope additional experimentation is planned. 

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3.6 Optical Design 

3.6.1 Design of Optics - This section provides the parameters of the 

optical design from which the design can be simulated analytically for 

evaluation. This report conforms to form MSM-S-201, 22 December 1966, 

The following items except as noted, are required by the above 

form and are given in Table 3.6.1-1, Lens Specification Data. 

Item 1. Curvature or radius of each surface 

Item 2. Aspheric Curvature Coefficients. All surfaces in the A/0 

telescope are spherical, therefore this does not apply. 

Item 3. Surface separations. This includes glass thickness, air 

spacings, pupil and stop locations, image or focal positions 

and other available cardinal points. 

Item 4. Glass types and/or indices of refraction. Note: the specified 

spectral wavelengths are given in Table 3.6.1-2 and 3.6.1-3 

(CLOC Specification). 

Item 5. Clear apertures and obscurations for each optical surface. 

Note: obscurations do not apply to the A/0 telescope. 

Item 6. All angular and linear dimensions on all prisms and mirrors are 

shown in Figures 3.6.1-1 through 3.6.1-4. 

Item 7. Optical dimensions, spectral data for all windows and filters - 

absorption or interference type, is presently under study. The 

dimensions for the window are shown in Figure 3.6.1-5 and those 

for the filter are listed in Table 3.6.1-1. However, the spectral 

data for the filters is to be determined by the Contractor. 

Item 8. Specification for coatings on each surface can be summed up as 

follows: 

a. On all refracting surfaces, single layer magnesium fluoride 

A/4 thick, where A equals 0.56 microns. 

b. Internal folding mirror, aluminized plus enhanced coating for 

98.5 percent reflectivity. 

c. External folding mirror, aluminized plus enhanced coating for 

93 percent reflectivity. 

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d. External scanning mirror, aluminized plus a SiO coating for 

87 percent reflectivity. 

e. Reflecting surfaces of the Pechan prism, aluminized plus SiO 

coating for 87 percent reflectivity. 

Item 10. The system optical layout is shown in Figures 3.6.1-6 and 3.6.1-7. 

3. '-,s 

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"FR 4.-4 tA C-rrETD WAVE. FRONT POwER 7 t Ri?EULACR'rrY WITHIN 10.10CA. 

t---Aoos,"/ 

ScA~E - '/a 

Figure 3.6.1-5 -7-0 .000 

Si hANILia.j' 

3. 440 
4 

c A y 

2 

Mi 

FI G U RE 3.6.1-6 Fl 

SPECIAL HANDLING 

SPECIAL HANDLING 
Si-t.CIALHANDLING 

N 

N 

" 

1 I 

I 

I 

! I 

I I.I 

SPECIAL HAN DLING 

TELESCOPE 
-NRO APPROVED FOR 

RELEASE 1 JULY 2015 

40 CLIC P 

ID HIPOW PJN 9300.62 DAT 

)RAT 9 3 5 1 0 

CS 3 5 3 5 1 3 

APS 1 

WV 6.5000100E-01 6.0500000E-01 5.6000000E-n1 5.1500000E-01 4.7000000E-01 

08J 8 5.0000000E-11 4.5461000E-03 5.0000000E+00 .000000000 

CF 2.540000E+04 Sr 5.000000E-03 

VIG1 

0 Cl .000001000 TH 1.00010,10E+11 AN 

1 CAO 9.0000901E+00 

1.61957119 1.62509838 1.6291413 1 N15 1.61757177 1.67198386 

1 CV 2.4918900-02 TH 1.3544000E+00 

2 CAD 6..990000064.00 

2 CV -5.4295000-07 TH 2.6560000E-01 AIR 

3 CAO 4.9200000E+00 

3 N15 1.60956076 1.61221404 1.61550439 1.61971365 1.62528070 

3 CV -5.6122100g- -02 TH 6.0000000E-01 

4 CAO 4.865010nFoon 

4 TH 7.8818000':+01 AIR 

4 RD 7.73610;0F+02 

5 CAS .000010000 3.6131060E-01 

5 CAO 5.0000000E+00 

5 AIR 

5 Cv .000000000 

6 CAO ,-+.000000'1E+00 

6 CV .000000000 TH 2.000(000E-02 AT,4 

7 CAS .000000000 2.9343194E-01 

7 CAD 5.000000^1:.+00 

7 AIR 

7 CV .0000)0000 

8 CAO .00000006.+00 

8 CV .00001'1000 TH 1.7006900E+01 AtR 

9 CAO 'i.0000001F+00 

9 CV .000001000TH 1.0047'356E+01 AIR 

10 CAS .000010000 4.46R7650E-01 

10 CAD 5.0000000F+00 

10 AIR 

10 CV .000000000 

11 CAO .0000000F+0o 

11 CV .000000000 TH 1.3374707F.-01 AIR 

12 CAS .000000000 4.51f-1000E-01 

12 CAD c,„000nonov+oo 

12 AIR 

12 Cv .00000c000 

13 CAO 5.000000:)F+00 

13 CV .0000011 000 TH 7.0000P00E-07 AIR 

14 CAD 5.0000000E+0o 

14 CV .00000n000 TH 5.71101-100E-0) ATR 

15 CAD S.000000cF4.00 

15 CV .00000'1 000 TH 1.200478E+01 ATP 

16 CAO 1.11000004400 

16 N15 1.51451 4?5 1.51601kAu 1.c,1 1 101H74 1.52044653 1.52359d2.8 

TABLE 3.6.1-2 " G. LOC- SPEc. IFIC_A Tiom qT I 2 7* 

SPECIAL HANDLING SECRET 3.4-/3 rR-IVAT. 

LENs 7,ESIGN KE-FEerAic' e°^"-Y) 

SPECIAL ; v 

pc. ) (1, re. 
L HANDLING SE.GRET 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Itek, 

16 CV 0.0 TH 9.1391000E+00 

17 CAO 7.7000000E-01 

17 CV .000000000 TH 1.017onn0E-01 AIR 

18 CAO 7.6000000E-01 

18 N15 1.51451425 - 1.5160444g1.51401874 1.520446`33 1.52359228 

18 CV 4.4823760E-01 TH 2.3410000E-01 

19 CAO 7.3000000E-01 

19 CV 4.5450700E-01 71-4 7.9157R90E-01 AIR 

20 CAO 6.4000000E-01 

20 N15 1.51451425 1.5160884q1.51801 874 1.52044643 1.52359228 

20 CV 0.0 TH 2.0000000E-01 

21 CAO 6.4000000E-01 

21 CV .00000nnoo TH 3.7249188E-01 AIR 

22 CAO 6.415000.)E-01 

1.61992119 1.62915413 

22 CV 1.9226366F-01 TH 3.9593292E-01 

22 N15 1.61752377 1.621983)46 1.62bn9838 

23 CAS 4.000000)F-01 5.0000nn0E-n3 

23 CAO 6.7900001E-01 

23 AIR 

23 CV -5.3806604-01 

24 CAO 6.620000nF-01 

1.699n54S3 1.70827343 24 N18 

25 N15 

1.68299="46 

1.61752177 1.619';2119 

1.647,17'494 

11((000E4;

"??(?n3 

1.'12.1 9A35.1.1 1.62Sn9k3m 1.6RR15413 

24 CV -7.3156413c-01 TH 2. 

25 CAO 6.7400001E-01 

25 CV 7.2421613v-01 TH 4.(i000000E-01 

26 CAO 6.4250001E-01 

26 CV -4.4399182-01 TH p.?734250E-01 AiR 

27 CAO Vi.4500001F-01 

27 N15 1.510i1425 1.51h00849 1.51801H74 1.5*?1,44671 1.52359224 

27 CV 1.4445R48'-01 TH 3.?000000E-01 

28 cA0 5.205000flE-01 

28 CV ■.6.9295932i;1-01 TH 3.7496143F-01 AIw 

29 CAO 3.2700001F-01 

29 N15 1.61543033 1.616612631;6 

6' 

1.62,4491 i.63488689 

29 CV -1.6232146:+00 TH 3.29S765?F-0 

30 CAO 3.305000- +-01 

30 CV -1.1136896c+00 TH 3.34?3?46F-01 AIR 

31 CAO 3.7200000E-01 

1.S1$191876. 1.5:).359228 

31 CV 9.7624414r-n; TH 3.?4c17630E-01 

1.5?1,446')3 31 N15 1.514S1.125 1.51604889 

32 CAO 1.9250000E-01 

32 CV "1.210914$4C.+00 TH 5.0000000E-0? A1H 

33 CAD 3.8750000E-01 

33 N15 1.61543033 1.618611 1.622630 1.6e).7-14951 1.630-16689 

33 CV -1.2523074;-- 4,00 TH 3.8131069E-01 

34 CAO 4.5350000E-01 

34 CV -2.9379211c-01 TH 1.H578450F+00 

35 CAD 4.9000000E-0I 

35 CV 9./765995F-01 TH 2.(177.3648F-01 

L.6141146669 35 N15 1.61543933 1.618612.h3 1.?262611 1.627q44D1 

36 CAO 4.900000, 4-_ -01 

36 CV 9.3330300E-01 TH 3.1/1158F.•-01 AIR 

37 CAO 9.9000000E-01 

37 N15 1.617 2177 1.61952110 1.6? 

37 CV 7./129147F-01 TH 3.0000nn0E-01 

19H3A 1.625194i3 1.62Rin413 

3. 6- /i PRIVATE 

rt.CIAL HANDLING 

TABLE 3.6.1- A/oriv (JED 
-NRO APPROVED FOR 

RELEASE 1 JULY 2015 

-3 

I AL HANDUNG --f4K-figt. 

)ftQiz; ' )1 ii•1 1)CSI 

38 CAO 5.8600000E-01 

38 CV 1.82923R1F.01 TH 1.5000000E=01 AIR 

39 CAO 5.9000000E-01 

. 39 N15 1.514514?5 1.516088891.51801474 1.52644653 1:52359228 

_ 39 CV o.n TH 1.7000000E-01 

40 CAO 5.9000000E-01 

40 CV .00000nonn TH 1.5000000E-01 AIR 

41 CAO 5.9000000E-01 

41 CV -5.0017106F-01 TH 2.0005154E-01 

1.91801874 1.52044653 1.52359228 

_ 41 N15 1.51451425 1.516n4H4g 

42 CAO 6.2000001E-01 

42 CV -2.4024916E-01 TH 1.0425652E+00 AIR 

- 43 CAO 7.5000001F-01 

43 CV .00000noon TH 2.0000000E-01 AIR 

44 CAO 7.7000000E-01 

1.64299c46 1.7082(343 44 N15 1.69226203 1.699a5453 

44 CV -1.3337190r-01 TH 1.A700000E-01 

1.68707398 

45 CAO 4.3500001E-01 

45 N15 1.61752177 1.61952119 1.62915413 

45 Cv 4.4379514E-01 TH 7.5600000E-01 

1.6219113H6 1.62509834 

___. 

46 CAO 4.7000000E-01 

46 Cv -5.6336474P-01 TH 7.6040145E-01 AIR 

47 CAO 4.4600000E-01 

47 N15 1.64312143 TH1.6;6:1, 1.66505028 

47 CV 4.549982:V-01 T1000E-01 °

1.65119990 1.6570900.4 

48 CAO 4.320000nE-01 

48 N15 1.61752377 1.61952119 1.62194346 1.62915413 

- 48 CV 4.6566261=--01 TH 5.8800000E-01 

1.6254433 

49 CAO 4.035000:E-01 

49 CV -3.3093167-02 TH 1.5000000E-0? ATR 

50 CAO 7.20500011 F-01 

____ 50 N15 1.61752377 1.61952119 1.62198386 1.6?915413 

50 CV 1.06978?5,7.no TH 5.0002125F-01 

1.6?509834 

51 CAD 4,.430on00E-01 

1.6870739q 1.6990,3453 1.76421343 51 N15 1.6H299c,f;') 1.6'47.26203 

51 Cv -4.3341200E-02 TH 1.4Q00000E"'01 

_ 

52 CAD ,i.o85n000E-01 

52 Cv 7.4291318c-ol TN 7.7157,471E-01 AIR 

53 CAO 1.500000 IF-01 

53 CV .0n0000000 ATP 

_ 

•0000U000 Tt-1 

54 Cv o.n TH 1.)0000n0F+00 

END 

_ * PUPL REAL 

* SPEC 

PECIAL HANDLING 

TABLE 3:6.1-2 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SPECIAL • DLING SECRET 

Ite ( 4 10 ical 1)( .1.H 

• CLIC P 

LOW POWER MODE 

ID MIPOw PJN 9300.62 DAT 

LENS NO. 660 

DRAT 9 3 5 1 0 0 

CS 3 5 3 5 1 3 

APS 9 

WV 6,5000000E-01 6.1,500000E-01 5,6000000E-01 5.1500000E-01 4.7000000E-01 

08J 8 1.2500000E-11 1.8180000E-02 1.2500000E+00 -1.4802315E+00 

CF 2.540000E+04 SF 5.000000E-03 

VIG1 .700 

0 CV .000000000 TH 1.0000000E+11 AIR 

1 CAO 5.0000000E+00 

1 N15 1.617521771,61952119 1.62194386 1.62509834 1.62915413 

1 CV 2.4918900E-02 TH 1.3544000F.00 

2 CAO 4.9900000E+00 

2 CV -5.4295000E-02 TH 2.6560000E-01 AIR 

3 CAO 4.9200000E+00 

3 N15 1.50956476 1.61221404 1.61550434 1.61971365 1.62528070 

3 CV -5.6122100E-o2 TH A.0000000E-01 

CAO 4.8650000E+00 

4 TM 2.8818000F+01 AIR 

4 RD 2.7361050F,02 

5 CAS .000000000 3.6131000E-01 

5 CAO 1.3950000E+00 

5 N15 1.61752377 1.61952119 1.621983861.62509638 1.62916413 

5 CV -1,1118446F-01 

6 CAO 1.3950000E+00 

6 CV 9.3433654F-02 TH 2.0000000E-02 AIR 

7 CAS .0000n0000 2.9343094E-01 

7 CAO 1.4000000E+00 

7 N15 1.61543933 1.61861263 1.62262630 

7 CV I.3135445F-01 

1.62/8491 1.63486689 

8 CAO 1.3950000E+00 

8 CV 2.0557867F-03 TH 1.3906900E+01 ATP 

9 CAO 1.030000nE+00 

9 CV .000000000 TH 1.0087256E+01 AIR 

10 CAS .000000000 4.468265(1F-01 

10 CAO 1.6400001E+00 

10 N15 1.61752377 1.61952119 1.62198 3- 86 1.6?509836 1.62915413 

10 CV -1.8305845F-01 

11 CAO 1.675000,1E+00 

11 CV -3.2199174E-01 TH 1.3374202E,,01 AIR 

12 CAS .000010000 4.5161010E-01 

12 CAO 1.6600001F4.00 

12 N15 1.61543433 1.61861263 1.62662630 1.62784961 1.63486689 

12 CV -3.3160336F-01 

13 CAO 1.7750001F...00 

13 CV -1.471228 -01 TH 2.0000000E-02 ATP 

14 CAO 1.H1b000)E+00 

14 N15 1.61752377 1.61952119 1.621RR3561.62509638 1.62915413 

14 CV 8.3476098F-02 TH 5.7110000E-01 

15 CAO 1.9150000E+00 

15 CV -5.3952257F-02 TH 1.2069578E+01 AIR -1 

16 CAO 1.1150000E+00 rRIVATE 

TABLE 3.6.1-3 ‘ ftEictiA p5A,/ irr -3 . 75)( 

HA DLIN0, 3.4-14 ( Z. EA/ E t.ov F c ff o 44-.1) 
SfrECIAL HANDLING "StefiLET-- 

TABLE 3.6.1-3 c. tv-rifv.et 3.4-47 

-NRO APPROVED FOR 

RELEASE 1 JULY 2015 

HANDLING 

RINtATE? 

_ 16 N15 1.51451425 1.5160888 .51801674 

16 CV 0.0 TH 9.1391000E.00 

17 CAO 7.7500000E-01 

17 CV .000000000 TH 1.0170000E01 AIR 

- 18 CAO 7.6500000E...01 

18 N15 1.51451425 1.51608889 1.51801874 

18 CV 4.4823760E-01 TH 2.3910000E-01 

19 CAO 7.2500000E-01 

- 19 CV 4.5450700E-01 TH 7.9157890E-01 AIR 

20 CAO 6.8000000E-01 . 

20 N15 1.514514251.51608889 1.51801874 

___ 

20 CV 0.0 TH 2.0000000E-01 

21 CAO 6.8500000E-01 

21 CV .000000000 TH 3.2289368E-01 AIR 

22 CAO 6.9150000E-01 

22 N15 1.61752377 1.61952119 1.62198386 

22 CV 3.9226366F-01 TH 3.9993292E-01 

23 CAS 8.0000000E-01 5.0000009E-03 

23 CAO 6.7900000E-01 

- 23 AIR 

23 CV -5.3506604F-01 

24 CAO 6.6200000E-01 

24 N15 1.6629q9AA 1.68707398 1.69226203 

- 24 CV -7.3156413F-01 TH 2.3100000E-01 

25 CAO 6.7400000E-01 

25 N15 1.61752377 1.61952114 1.62198366 

25 CV 7.2421613F-01 TH 4.5000000E-01 

26 CAO 6.8250000E-01 

26 CV -4.4399182F-01 TH 2.2738000E-01 AIR 

27 CAO 6.4500000E-01 

27 

27 CV 

 N15 1. 51451425 1.51608889 1.51801874 

3.4445848F-01 T4 3.20000°0E-01 

28 CAO 5.2050000E-01 

28 CV -6.9295932F-01 TH 3.7496183E-01 AIR 

___ 29 CAO 3.2700000E-01 

29 CV -1.0232146F.00 TH 3.q95/652E-01 

29 N15 1.61541933 1.01861261 1.62202630 

30 CAO 3.3050000E-01 

___ 30 CV -1.1136896F+00 TH 1.3421000E-01 AIR 

31 CAO 3.7200000E-01 

31 N15 1.51451425 ;91801874 

31 CV 5.7628414F-01 TH"T=630E-0 1

32 CAO 1.4250000E-01 

32 CV -1.2109148F+00 TH 5.0000000E-02 AIR 

33 CAO 3.875000(1E-01 

33 CV -1.2523n7qv+on TN 3.9331n69E-0 .

33 N15 1.61541q33 1.6186)261 1622626130 

34 CAO 4.5350000E-01 

34 CV -2.9379213F-01 TH 1.8578400F+00 AIR 

____ 35 CAO 4.9000000E-01 

35 N15 1.61543933 1.61661261 ;6 622 2630 

35 CV 5.7765995F-01 TH 2.072360 44E36 CAO 4.900000^F-01 

- 36 CV 9.3330300E-01 TH 3.1781356E-01 AIR 

37 CAO 5.900000nF-01 

37 N15 1.61752177 1.61992119 198386 

1.52044653 1.52359228 

1.52044653 1,52359228 

1.52044653 1.52359228 

1.62509838 1.629)5413 

1.69905453 1.70427343 

1.62509838 1.62913413 

1.52044653 1.52359228 

1.62784951 1.63488684 

1.52044653 1.5235'4228 

1.62784451 1.63486684 

1.62784951 1.63488689 

1.62509838 1.62915413 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

HANDLING SECRET 

37 CV 7.7129187F-01 TH 3.0 01 

38 CAO 5.8600000E-01 

38 CV 1.8292381F-01 TR 1.5000000E-01 AIR 

39 CAO 5.9000000E-01 

39 N15 1.51451425 ' 1.516088891.51801874 1.52044653 1.52359228 

39 CV 0.0 TH 1.7000000E-01 

40 CAO 5.9000000E-01 

40 CV .00000(1000 TH 1.5000000E-01 AIR 

41 CAO 5.900000E-01 

41 N15 1.51451425 1.51608889 1.51801874 1.52044653 1.52359228 

41 CV -5.0017106r-01 TH 2.0005154E-01 

42 CAO 6.2000000E-01 

42 CV -2.4024916F-01 TH 1.0425652E+00 AIR 

43 CAO 7.5000000E-01 

43 CV .000000000 TH 2.0000000E-01 AIR 

44 CAO 7.7000000E-01 

44 N15 1.68299586 1.68707398 1.69226203 1.69905453 1.7082(343 

44 CV -1.3337190F-01 TH 1.6700000E-01 

45 CAO 8.3500000E-01 

45 N15 1.61752777 1.61952119 1.62198186 1,62509838 1.62915413 

45 CV 8.4379514E-01 TH 7.5600000E-01 

46 CAO 8.700000GE-01 

46 CV -5.6336878E-01 TH 7.5040185E-01 AIR 

47 CAO 8.8600000E-01 

47 N15 1.64312043 1.64668350 1.6;119990 1.65709009 1.66505028 

47 CV 4.5499823E-01 TH 2.)000000F-01 

48 CAO 8.3200000E-01 

48 N15 1.61752377 1.61952119 1.62198386 1.62509838 1.62415413 

48 CV 8.6566261E-01 TH 5,8800000E-01 

49 CAO 8.0350000E-01 

49 CV -3.3093167F-02 TH 1.5000000E-02 ATR 

50 CAO 7.2050000E-01 

50 N15 1.61752377 1.61952119 1.62509838 1.62915413 

50 CV 1.0697825E+00 TH 5.0002125E-0 ;62198386 

51 CAO 6.4300000E-01 

51 N15 1.68299586 1.68707398 1.69226203 1.69905453 1.7082(343 

51 CV -8.3341200E-02 TH 1.4900000E-01 

52 CAO 5.0850000E-01 

52 CV 7.4291318E-01 TH 7.7157971E-01 AIR 

53 CAO 1.5000000E-01 

53 CV .000000000 TH .000000000 AIR 

54 CV 0.0 TH 1.0000000E+00 

END 

• PUPL REAL 

• SPEC 

3. -/1 SPECIAL HANDLING SECRET 

TABLE 3.6.1-3 Ivr I A, 1) Eb 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

VIAIFER 9300.62 

/2.7.o 

Si-LCIAL 

C. 0 61L.t T a 

SYs rem 

TANGENT I AL FANS SAGI7TAL FANS 

FULL FIELD 

lfi 

0 O

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ROY TRACE SPEC;IAL HANDLING -SE-64E4 Fig

. 3h.1-$- ANGULAR A BERRATION AT 127)( 3.4--/9 

ENTRANCE 

PUP IL 

ODS0 RADIANS .4 

_ Vs. 

Votu,_ 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

;P, 

‘, - 4.c. 7 A SPECIAL. 1-it-ti '41.46_ 1111/4.i -SEettcr , 

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Fig. a6.1-T ANGULAR ABERRATION AT 84.6,7 )( 

ENTRANCE 

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NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3.sx SPECIAL HAimuLING 4yEeffET-- 

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659 EN SFIT1 NRO APPROVED FOR 

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FULL FIELD 

Y EN 

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NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SPECIAL FIA7

NDLING 

2./ ./ 

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SHAFER 9300.62 06/06/676 

L 1J 

Fig. 1.6.1-12 

RAY TRACE SPECIAL HANDLING SECKI 34-23 

- ANGULAR ABERRATION A T 21.17A 
TANGENTIAL FANS 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

is. it tx SPECIAL Hitilii_LINQ,ELCRET 

4.0A4p4. c TE 

SHAFER X300.62Z. . SY MAI 06/06/67. 

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Fig. 3,0.1-13 

Y EN 

00 le A t) t ACS 

. 41 

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RAY TRACE SPECIAL HANDLING SECRET 

-ANGULAR ABERRATION AT 15. 88 

r r 9 

ENTRANCE 

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3. t-24 
• 

SHAFER 9300.6Z 04/06/67* 

TANGENTIAL FANS 

FULL FIELD 

• ‘51,— 

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SAGI7TAL FANS 

0 01Z0 2:13S 

0 0 

oa 

NJ 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SPECIAL .ANDLINQ SECRD 

O., FIELC: 

YEN 

0 

0 

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0 

0 

2 0 

NJ 

w A v eS 

EN 

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t X EN DPD 

/ 47 

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2.COOD 

AX 

PRIVATE 

EN ---+ 

SPECIAL HANDLING 

RPY TRP,CE (NPD - OPTICAL PATH 01=FERENCE) 

A - 

Fig._Ah.1-14 - OPTICAL PATH DIFFERENCE AT 12-7 3. i- 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SF LC;IAL HAN bl...11 :JECRET_ 

84.(.-7A 

SHAFER 9300.62 

PR VAtE 

04/06/47.1 

TANGENTIAL FANS S: 

45 ■•• .451, 

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SAG I TTAL FANS 

CD 

CD 

V 

0 N 

0 0 0, 

0 

r 

2 

2 Cal 

0, 

0 r 6

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ON AXIS 

I 

X EN 5PD 

_ 2.0000 

PRIVATE 

A • X EN 

3.4-24 RAY TRACE (61PD = EFT I CFA19-11617FAAMPLING SECREf 

Fig._ 3.6.1-15 — OPTICAL PATH .DIFFERENCE AT 84.67 X 

Y EN 

Y EN 

ENTRANCE 

PUP IL 

2.0000 u/AvES 
6 r 

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TITLE. 

Prescription for Optical System 

USE 

To evaluate ability of proposed design to 

meet requirements 

MSM-S-201 

A 22 Dec. 1.966 

OF r ICE OF Pl/imARY 

I Y 

Major Suncoairle 

Project n2,11,L. 

H, p 1 1,W.C$ 

Mit rt176LA rIONShi, 

The prescription will later become Part of 

the specification. 

Tho Subcontractor shall proparc a prescription which completely 

describes the parameters of the optical system from which the 

system can be simulated analytically for evaluation. It shall 

include the following information: 

1. Curvature or radius of each surface. 

2. Aspheric curvature coefficients per the aspheric sag expression 

/z = 

l 

+ y (3 Y. t‘y 

where (eis the vertex curvature per (1) above, tt is the conic 

coefficient = 1 - e2 and e is the conic surface eccentricity. 

3. Surface separations. This includes glass thickness, air spacings, 

pupil and stop locations, image or focal positions and other 

available cardinal points. 

4. Glass types and/or Indices of refraction with specified spectral 

wavelengths. 

5. Clear apertures and obscurations for each optical surface.. 

6. All angular and linear dimensions on all prisms and mirrors. 

■MINIONIIft 

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ASM-:i-201 

2.4;.,e 2 

7. Optical dimensions, spectral data for all windows and filters -

absorption or interference type. 

8. Specification for coatings on each surface. 

9. Tolerances on 

a. Spacings 

h. Thickness 

c. Curvatures 

d. Aspheric coefficients 

e. Surface tilts and misalignments 

10 System optical layout (drawings), with proper identitication of 

surfaces by number, spacing, etc. 

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Pages 3.6 - 55 through 3.6-63 deleted 

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3.6.3 Objective Lena Design Optimization 

Introduction 

The A/O doublet objective lens has been designed for maximum performance and 

minimum weight. A special glass (KzFSN-4) has been used to minimize the secondary 

color, which is the limiting on-axis aberration. This section will, therefore, 

show that the A/O objective design is optimized for these considerations as well as 

overall axial performance. 

Discussion 

In an achromatic doublet, the upper and lower wavelengths, designated here as C and 

F, are united at a common focus. The question then arises as to whether the other 

colors will also be united at this focus. To discover this, the value of 1 ' D- / ' F, 

which is defined to be longitudinal secondary spectrum, or secondary color, may be 

calculated where D is generally assumed to be the major or peak wavelength and 1 ' is 

the back focal length for a given wavelength. For an object at infinity, the longitudinal 

secondary spectrum is given by 

1' -1' = v Pa - Pb 

D F Va - Vb 

where 

f' = focal length of the achromatic doublet 

a = designates the first element 

b ., designates the second element 

partial dispersion = nF nD 

n

F - n 

and V reciprocal dispersion = nD - 1 

nF- nc 

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The secondary spectrum of most thin achromatic doublets, made out of 

common glasses, is approximately the same and is given approximately by 

D 

- 1 ' F 

fl 

2500 

However, there are a few special glasses such as the "short flints" in which 

the partial dispersion is somewhat smaller than normal. Such a glass can be combined 

with a normal crown to make an achromatic doublet with reduced secondary spectrum. 

Many of these glasses, however, have undesirable chemical and physical properties and 

are available only in small diameters. 

In addition to secondary spectrum, spherical aberration and the chromatic 

variation in spherical aberration must also be considered in optimizing axial performance. 

DesignA s Considered 

Several designs were considered in the analysis. All the designs presented 

here have a 10 inch diameter entrance pupil and are evaluated over a 1.042 degree field 

of view (63. 5X case) and over the 0.47 to 0.65 micron spectral region. Some of these 

designs were evaluated at the reticle and include the Pechan prism and the field lens. 

Others consider only the objective lens. However, the case of the objective alone ill,- 

directly comparable to that of the objective, Pechan prism and field lens 

combination, since only a lsight modification is required to compensate for these 

extra elements. This modification is approximately similar to adjusting the 

design to compensate for a plea - parallel plate. 

The first doublet considered was one consisting of common glasses, namely 

- ; 

SK-16 and F-2. The lens specification data for this design is presented in Figure 3.6.3-1 and 

0.. - 

the corresponding optical path difference plots are presented in Figure -3.6.3-2. 

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It is seen that although this design hasvery good spherical correction at 

0.56 microns, the chromatic variation of spherical aberration and the 

secondary spectrum are very large and could not be tolerated. 

The second design considered was one in which a "short flint" KzFS-5 

was used with a common crown SK-2. This design (see Figure 3.6.3-3 and 3.6.3-4), 

although not quite optimized, shows a considerable reduction in secondary 

spectrum and in chromatic variation of spherical aberration. It is also 

at a tolerable state of chromatic correction. 

The glasses used in a design concept were SK-2 and KzFS-5. However, 

after many discussions with Schott and others about the "short flints", it 

was learned that KzFS-5 had undesirable physical properties and that KzFS-4 

was the most desirable of these glasses for consideration. 

The next design considered was an SK-2 and KzFSN-4 doublet. The lens 

specification data for this design and the corresponding optical path 

difference plots are presented in Figures 3.6.3-5 and 3.6.3-6, respectively. 

From Figure 3.6.3-6, it is seen that the performance of this design is 

comparable to that of the previous design. However, since the index of 

refraction of KzFSN-4 is lower than that of KzFS-5, steeper curvature is 

required for optical correction. This demanded an increase in central 

thickness and thus the weight increased approximately 3 pounds from the 

previous design. 

The next design consideration was to try and match a common crown 

with an index slightly higher than SK-2 with KzFSN-4 to reduce the weight 

and also to achieve good optical correction. It was then found that 

SK-16 and KzFSN-4 combination rendered an optimum axial correction and 

also weighed approximately two pounds less than the 

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SK-2 and KzFSN-4 design. These glasses were then used in the final design and 

the performance of the final A/O objective system at the reticle is presented in 

Figure 3.6.3-7. It can be seen that the system is diffraction limited at 

0. 56 microns and has good chromatic corrections. 

Conclusion 

The A/O objective lens has been designed for maximum on-axis performance and minimum weight. To achieve satisfactory axial performance, it was 

necessary to use a short flint. However, the optical correction achieved did not 

vary significantly for the two short flints considered. Since KzFS-5 has undesirable 

physical properties, it was necessary to use KzFSN-4. The optical correction of 

several crown in conjunction with KzFSN-4 also stayed about the same. SK-16 was 

then chosen since it minimized the weight of the doublet and rendered good axial 

performance when combined with KzFSN-4. 

A triplet design, which resulted in a 5% improvement in on-axis resolution 

is described in Section 3.6.2. 

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LENS NO. 18 

SYSTEM DATA 

F-NUMBER = 

FOCAL LENGTH = 

PACK FOCUS = 

TOTAL LENGTH 

EXIT PUPIL DISTANCE = 

GAUSSIAN IMAGE HEIGHT = 

1.5373 

79.8950 

293.4845 

,6710 

ENTRANCE PUPIL DISTANCE = 

OBJECT HEIGHT = 

CHIEF RAY ANGLE 

CHIEF RAY POSITION = 

AXIAL REAM RADIOS = 

UP/Dv 

-1,U1dE 0 

.009 

5.000 

0 00 

WAVELENGTHS LOWER .4700 MAJOR ,5600 UPPER .6500 

SURFACE DATA 

SURFACE 

NUMBER 

OBJECT 

RADIUS OF 

CURVATURE 

INFImITE 

1 48,8086 

2 -31.3916 

3 -30.1219 

4 -625,0714 

5 -6.4535 

6 6,7753 

7 4.8786 

8 15.0681 

9 INFINITE 

10 -16.6987 

11 -3.9569 

12 -3.7132 

13 -14.0737 

14 9.2453 

15 -12.6200 

16 INFINITE 

THICKNESS 

2,000E 09 

1.0075 

.2933 

.6000 

APPROXIMATE 

N(D) V(D) 

AIR 

1.020414 5k---“0 60,30 

AIR 

1.620051 F- Z-- 36.35 

APERTURE 

DIAMETER 

10.0000 

9,9809 

9,0907 

32,7764 AIR 4,0281 

.6613 AIR 6,e2231 

.0091. AIR 6,0130 

.2934 AIR 5.9/61 

13.2325 AIR 6,U239 

6.4604 AIR 4.673 

,4466 AIR 3 .d52 0 

.1337 AIR 3.6452 

.4516 AIR ,i.H341 

.001n AIR 3.7372 

,4712 AIR 3./019 

12.4411 AIR 3.68',2 

9.1391 1.516799 64,24 2..?6H2 

.L;IAL 1-45/P,Vi I \i ■-\ crn.,,t,,0 RET 

Table 3.6.3-1iens Specification Data for SK-16 and F-2 Doublet 
R 

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17 INFINITE n AIR 1.59 05 

18 R.2419 .2391 1.516799 64.24 1.586'4), 

19 11.1674 1.5373 AIR L.5542 

IMAGE INFINITE 

Table 3.6.3-1Continued 

3. L - 
CNTPANLE 

7 

; 

\ 

) 

/ 

---______---- 

I 

1'1 P D 

Z.CSCO 

.CN 

_ 2.00CC 

EN 

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HAGERM 7>300.61 09/02/C7* 

FACOTTAL FAN 

Y 

EN 

ON AXIS 

3.4-70 RO)/ TRACE PD - GPTICAL TH31,-,-CPLNCC) 

Table 3.6.3-2 Optical Path Difference at Reticle for SK-16 E71. 

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UNITS - INCH TTL - 76. 4

2

3

96 

F /No 7.61 G.I.P. .6799 FOC. LFNGTH 

WV mAjOR - .5800 WV UPPER - .6q00 WV LOWFP - 

.4 700 

TN mAj V C. A. DIA. 

0 !NRINITF +9.9P9D+010 Ayr? .000 P 

114.8 111 1.3000 1.609,11 c0•20 10.005 P 

2 -19.9804 .1654 ATP 9.976 P 

-19.9149 .4800 1.8C 0 KzPS-535.07 9.897 P 

4 -370.3987 74 .4785 A lp 9.834 P 

Table 3.6.3-3 Lens Specification Data for SK-2 and KZFS-5 

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TANGENTIAL SA GI 

FvLL FIE t.D 

0.7 F EL. b 

/.4 7 

C,n, - 4)(15 

"2-.0A 

Table 3. 6. 3-4 Optical Path Difference for SK-2 and KZFS-5 

3. g- 72 

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riNn. - 7.al - .700 FOC. LENGTH - 

WV "Ajnp - .5600 wv vIDDEp - WV Lnwrp - .4700 

SN p Tu N NIA I V C. A. DIA. 

0 1 HP. 1 N I IF +0.000D+010 AIP '.000 R 

I.R410 1.600q1 SK-2_ 50.20 10.004 P 

.0209 ATP 0.875 P 

.4c400 I •q I Sc.') KTF-sfv43a.17 P.gss p 

+0.0('01)4000 ATP g.8'.,8 p 

INFT.ITF 7,1.670g AID u.A57 P 

nPAG 

Table 3. 6. 3-5 Lens Specification Data for SK-2 and 

KZFSN-4 Doublet 

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? -I3.3q07 

3 -11.1477 

4 -11.F,00 7 
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\._ 

----,_ -- ---- 

2 . Lort.k. 

Table 3.6.3-6 Optical Path Difference for SK-2 and KZFSN-4 

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HAMS ,300.42 02,05/474 

TOMMEHRIAL FaMS SAGITTOL FAS 

0 

O 

3 

VI 

Y Erg --4 

EATRANCE 

PUP rL 

2 .0000 

X EN 

RAY TRACE CI PD =err Ica. PATH 0 1FFBOVICE) 

3.4- 7.1" 

Table 3.6.3-7 Optical Path Difference for 9300 SK-16 and 

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3.6.4 Illumination Studies 

This section presents the results of two studies. 

1. The vignetting of the interior optical train of the final 

A/0 telescope. This study does not consider vignetting due 

to the external scan mirrors. 

2. Spot diagrams are shown to illustrate the exit pupil shape 

versus field angle and color correction. 

Internal Vignetting 

The vignetting in the A/0 zoom telescope was calculated 

at the peak wavelength (0.56 microns) and also throughout the visible (0.47 - 

0.65 micron) spectral region. At the peak wavelength, 253 rays were traced 

at normalized field positions of 0.0, 0.5, and 1.0, since the transmission 

specifications are given at these field positions. To calculate the 

vignetting over the visible spectral region, 70 rays were traced at each of 

the following wavelengths 0.65, 0.605, 0.56, 0.515, and 0.47 microns. In 

both the monochromatic and polychromatic cases, the rays were traced at six 

magnifying powers, namely, 127X 84.67X, 63.5X, 31.75X, 21.17X, and 15.88X. 

The percent vignetting for all these different cases is given in 

Figure 3.6.4-1 where 

Vignetting = Rays in - Rays out 

Rays in 

Spot Diagrams - Spot diagrams of the exit pupil which are 

symmetrical about the Y-axis, for these different cases are presented in 

Figures 3.6.4-2 through 3.6.4-7. From these spot diagrams, it should be 

noted that the exit pupil grows with field angle. This is the result of 

pupil aberration which allows a slightly larger tolerance on eye position 

during observation without effecting system performance in any other way. 

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POWER 

MONOCHROMATIC % VIGNETTING 

A = 0.0 7 = 0.5 7 = 1.0 

POLYCHROMATIC % VIGNETTING 

1T= 0.0 7= 0.5 TT = 1.0 

127X 0.0 0.0 0.0 0.0 0.0 0.0 

84.67X 0.0 0.0 0.0 0.0 0.0 0.0 

63.50X 0.0 0.0 20.2 0.0 0.0 19.2 

31.75X 0.0 0.0 0.0 0.0 0.0 0.0 

21.17X 0.0 0.0 0.0 0.0 0.0 0.0 

15.88X 0.0 0.0 19.0 0.0 0.0 20.3 

where TT= normalized field position 

% vignetting = Rays in - Rays out X 100% 

Rays in 

Figure 3.6.4-1 , % Vignetting in Interior Train of 9300 Zoom 

Telescope. 

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Spot Diagramof Ex it Pupil at 127X 

Figure 3. 6.4-2 

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ft • • • • • 

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Figure 3. 6. 4-4 

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4-5 Spot Diagrams of Exit Pupil 

(NJ 

3.1-81 

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• 

1= 

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• 

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SPECIAL HANDLING --SEGRE-T-- 

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3.6.5 Fabrication and Alignment Tolerances 

Introduction 

This section presents the optical fabrication and static alignment 

tolerances for the final A/O zoom telescope design 

A schematic diagram of the system at 31. 75X is presented in Figure 3.6.5-1. 

These tolerances are based upon the preliminary tolerance budget, 

copy of which is presented in Figure 3.6.5-2 

It is to be noted that the power changer tolerances are not included in this budget 

since the resolution requirements are given only at 127X. However, tolerances 

have been assigned to the power changer on the basis of minimizing the apparent 

change in resolution observed at the eye. 

It must be also be noted that the tolerance budget presented in Figure 3.6.5-2 

assumes that actual measured radii and thicknesses will be used in the melt design 

and that the system will be "tweaked" up by adjusting certain airspaces to be 

determined. An additional assumption used here is that the system will be focused 

for the best on-axis focal position. 

The mathematical assumptions employed in this tolerance analysis are the 

following. The tolerance on each optical parameter introduces some 6 0. P.D. 

(optical path difference) degradation into the final wavefront. The amount of this 

error has been calculated for each parameter. If the signs of the errors are 

assumed to have a random distribution and the errors add in a random fashion, then 

the probable degradation of the final wavefront due to the cumulative effects of n 

optical tolerances will be: 

0. P. D. peak to peak 

n 

( 60. P. D.

1/2 

peak to peak) 

1= 1 

. 

In other words, the expected cumulative error is the square root 

of the sum of the squares of the individual errors. 

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Radius, Thickness, and Airspace Tolerances 

The radius, thickness, and airspace tolerances for the complete telescope 

are presented in Figure 3.6.5-3. 

In section 

lv , 

3.6.1-4 it is shown that the objective airspace ∎may be varied by as much 

r 

as t 0.050 in the melt design depending on how well objective elements (indices) can 

be matched. An additional tolerance that must be imposed is that in the high power 

mode the airspace between the objective and the Pechan prism must have the value 

of 67.1797 inches t 0.1000 inch. 

Element and Group Tilts and Decenters 

An element tilt refers to the alignment of that element relative to the 

mechanical axis of the lens cell. A group tilt refers to the alignment of the 

mechanical axis of a lens cell (containing several elements) relative to the optical 

axis of the system. All elements are assumed to be tilted about their geometrical 

centers. Lens cells or groups, on the other hand, were rotated about points supplied 

by Engineering. The distances of these centers of rotation from the centers of the lens 

cells are given in Figure 3.6.5-4. " 

Similarly, an element decenter refers to the parallel translation of the axis 

of the element relative to the axis of the lens cell. A group decenter refers to a 

parallel translation of the axis of the cell relative to the optical axis of the system. 

Element and group tilt and decenter tolerances are given in Figure 3.6.5-5. 

Wedge Tolerances 

The wedge tolerances for Individual elements are given in Figure 3.6.5-5 in terms 

of total indicated runout (TIR) measured in inches at the edge of the element. In 

addition, all cementing layers must have a wedge of less than . 0002 inch TIR. 

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Surface Irregularities 

The maximum allowable surface irregularities are presented in FigureA3.6.5-6 

where the surface irregularity is defined to be the peak-peak deviation of the 

surface being tested from the nearest sphere over any circle having a diameter 

equal to the axial beam diameter. For the elements other than the power changer, 

the 127X axial beam diameters are to be used. This data is presented in Figure3.6.5-7 

For the power changer, the 15.88 X axial beam diameters should be used. This 

data is presented in Figure 3.6.5-8. 

Power Tolerance 

Power (test plate match) is the deviation of the nearest sphere of the test 

plate over the clear aperture. All surfaces in the A/O telescope must be held to a 

power tolerance of X /4 peak to peak except for the two external mirrors and the 

internal mirrors which must have power tolerances of X /10 peak to peak and the Pechan 

prism surfaces which must have power tolerances of X/8 peak to peak. 

Glass Quality . 

The Pechan prism glass should be Schott Grade 4 and the rest of the elements 

Schott Grade 2. 

Conclusion 

The 9300 telescope has been toleranced on the basis of minimizing the cost of 

fabrication and alignment while keeping the expected wavefront deformation within the 

limits specified in the presented tolerance budget. 

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SPECIAL HANDLING 

Group Surfaces 

Distance of rotation point from 

first surface of group 

1 1,2,3,4 + 1.10 inches 

2 5,6,7,8 + . 34 inches 

3 10,11,12,13,14,15 + .80 inches 

4 20,21,22,23,24,25,26 + 1.68 inches 

5 27,28,29,30 + 1.59 inches 

6 31,32,33,34 - . 50 inches 

7 35, 36,37,38 + .94 inches 

8 44,45,46,47,48,49,50,51,52 -.50 inches 

* Note that surfaces 39 and 40 (the filter) and surfaces 41 and 42 (last relay 

element) are both elements and groups. The element tilt data is given in 

Figure 5. 

Figure 3.6.5-4 Assumed Centers of Rotation 

for Lens Cells 

3.6 -92 

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SPECIAL HANDLING --K-GRET- -- 

Surface * Individual Surface 

Refracting Irregularity Contribution to Wavefront 

Elements Surfaces Peak - Peak Peak - Peak 

Window 2 X/10 X /20 

Objective 4 X /10 X /20 

Power Changer 10 X /8 X /16 

Field Lens 2 X /20 X /40 

Pechan prism 4 x /20 X /40 

Reticle 2 X /20 X /40 

Zoom relay-eyepiece 26 ** N. /20 X /40 

Surface Individual Surface 

Reflecting Irregularity Contribution to Wavefront 

Elements Surfaces Peak - Peak Peak - Peak 

External Mirrors 2 X /12 X /6 

Internal Mirror 1 X /16 X /8 

Pechan prism 5 X /20 0.15 x cos i where 

i = angle of incidence 

Surface irregularity is the peak - peak deviation of the surface being tested 

from the nearest sphere over any circle having a diameter equal to the axial 

beam diameter at 127X. 

** Cemented surfaces were neglected. 

Figure 3.6.5-6 

3.4-94' 

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SN 

Axial 

Beam Dia. SN 

Axial 

Beam Dia SN 

Axial 

Beam Dia. 

1 10.00 in. 19 0.13 in. 37 0.12 in. 

2 9.87 20 0.02 38 0.11 

3 9.74 21 0.00 39 0.09 

(assume . 02 in. ) 

4 9.68 22 0.05 40 0.09 

5 23 0.08 41 0.07 

6 24 0.08 42 0.06 

7 25 0.11 43 0.0 

8 26 0.15 44 .0.01 

9 27 0.17 45 0.02 

10 28 0.20 46 0.05 

11 29 0.20 47 0.05 

12 30 0.24 48 0.05 

13 31 0.25 49 0.10 

14 32 0.24 50 0.10 

15 33 0.24 51 0.10 

16 0.95 34 0.24 52 0.08 

17 0.16 35 0.14 53 0.08 

18 0.15 36 0.14 

Figure 3.6.5-7 127X Axial Beam Diameters 

3.4-95 

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%.)i 11.)LI1`v6 ""j'EEIRET-- 

SN 

Axial 

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5 1.50 in. 

6 1.50 

7 1.60 

8 1.60 

9 2.00 

10 2.40 

11 2.50 

12 2.44 

13 2.52 

14 2.52 

15 2.52 

Figure 3.6.5-8 15. 88X Axial Beam Diameter for Power Changer 

3. - 96 

(ri't vATE) 

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3.6.6 Optical Transmittance 

This is a study of the transmittance of the complete A/0 telescope 

system, including one internal mirror, two external mirrors, and the window. 

The transmittance calculation takes into account the absorption and reflection 

losses of each individual element, and examines the variation of reflection and 

absorption with the glass type and the angle of incidence of the light at each 

surface. 

The total transmittance of the complete A/O telescope system has been 

calculated and found to be 35.4% for the 127 X (high power) mode and 31. 2% for 

the 31. 75 X (low power) mode. The following assumptions were made: single 

layer magnesium fluoride anti-reflection coatings on all refracting surfaces, 

both external mirrors are aluminized and have a SiO protective coating (87% 

reflection each), the internal folding mirror aluminized with a 2-layer enhancement coating (93% reflection), and multilayer coatings (98. 5% reflection) on two 

surfaces of the Pechan prism. The transmittance calculation takes into account 

the expected reflection and absorption losses of each element, rather than the 

theoretically predicted values. The performance assumed for the single layer 

magnesium fluoride coatings, for example, is based on actual measurements made 

on coatings on different index glasses. Although the variation of reflection with 

glass index and angle of incidence of the light are considered, the effects of vignetting 

and filters (aside from surface reflections) has been ignored. 

SPECIAL HANDLING SCCRCT 3.6-97 
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SPECIAL HANDL? 3 SCC: 

Before proceeding with the actual transmittance calculation, it is important 

to establish the effect of the angle of incidence of light on the performance of the 

anti-reflection coatings. 

The change of the reflectance of a X /4 one layer anti-reflection coating as 

a function of the incident angle of the light was computed using a multilayer film 

analysis program on the computer. The results show that the transmission of the 

film changes by about 0. 1% (for example, from 99.5% transmission to 99.4%) as the 

angle of incidence of the light goes from normal to 30°. 

Angle of 

Incidence 

Anti-Reflecting Surfaces 

1.52 

- Magnesium Fluoride 

Transmittance 

of one surface 

1.69 

o 0 

Substrate Index of Refraction 

1.62 1.65 

98.74% 99.35% 99.49% 99.64% 

5

o 98.74% 99.35% 99.49% 99.64% 

15

o 98.73% 99.34% 99.48% 99.64% 

25° 98.68% 99.29% 99.43% 99.58% 

35° 98.50% 99.10% 99.23% 99.38% 

45

o 97.93% 98.53% 98.66% 98.81% 

practical value 98.4% 98.8% 99.0% 99.3% 

3. 4 - 98 - 

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_ 

Now the angles of incidence of the on-axis rays have been tablulated for 

each refracting surface of the A/O telescope for both the 127X (high power) mode, 

and the 31. 75X (low power) mode. The average angle of incidence of the marginal 

ray is 4.0° for the high power mode and 5. 1° for the low power mode, and none 

of the angles are above 30° in either mode. 

For these reasons, we can say that the reflection losses for the whole 

axial beam will be indistinguishable from the losses of an axial pencil at normal 

incidence to all the surfaces. A similar type of analysis has been done for the offaxis beams, where the angles of incidence at the surfaces are higher, and the 

conclusion is that the off-axis reflection losses for refracting surfaces will be 

less than 2. 0% greater than the axial reflection losses. When the transmission of 

the whole system is considered, this variation of transmission with field angle 

becomes less than 1%, i. e. the transmission at full field in the Thigh power mode 

will be between 34.4% and 35. 4%, where the latter figure is the axial transmission. 

For these reasons, the variation of the transmission of the complete A/O 

telescope with field angle is considered negligible. The results obtained by the 

following analysis are, therefore, valid across the field. 

A summary of assumed reflection losses for every surface in the system, 

as well as the results of the cumulative reflection loss calculation are shown in 

Figure 3.6.6-1. Most of this information was taken from G. R. Wirtenson' s memo, 

"Coating Thruput Values (Project 9300)", July 27, 1967, which is enclosed as 

Addendum 3.6.6-A. 

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Absorption losses are not as great as reflection losses, but are significant 

enough to be analyzed. There are approximately 20.0 inches of glass which light 

must pass through, in the low power mode, before reaching the eye (counting the 

unfolded length of the Pechan prism and the window). Of this 20.0 inches of glass, 

roughly 11.8 inches consists of low index glasses like BK-7, the other 8.2 inches 

are high index glasses, such as SK-16. The transmission of these glasses and the 

resulting absorption calculation are shown in Figure, 3.6.6-2 

the source of the data used. 

Figure 3.6.6-3 shows a summary of the results, and the calculation of the transmittance of the whole system, combining the effect of reflection and absorption losses. 

The value of 35. 4% transmittance for the whole system in the high power mode for the 

major color represents the product of 39.2% transmission due to reflection losses 

alone and 90. 2% transmission due to absorption losses alone. 

If the internal folding mirror were coated with the same multilayer 

dielectric stack (98. 5% reflectance) as the Pechan prism faces, instead of aluminum 

and a two-layer enhancement coating, the transmission would rise from 35.4% and 

31.2% (for the high power and low power modes respectively) to 37. 5% and 33. 0%. 

Because of the hostile environment, little can be gained by trying to use 

better coatings on the external mirrors. 

In the real case, we must trade off the ideal transmission versus that required 

to meet the specification, schedule and cost. Durability and reliability of the coatings 

are of prime importance. 

3. 4 -/00 HANDLII\iG SECRET 
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RELEASE 1 JULY 2015 

_ rir..CIAL HANDLING -SteRffThe study has been carried further based upon the trade-off considerations, 

and the following critical items were considered. 

1. The Pechan prism reflecting surfaces coated with aluminum plus a 

protective coating for 87% transmission. 

2. The internal fold mirror coating to be enhanced for 98. 5% reflection. 

3. The external scanning mirror to be coated with aluminum and SiO 

for 87% reflection. 

4. The external fold mirror coating to be enhanced for 93% reflection. 

5. All other element surfaces to be coated with magnesium fluoride for 

X /4 where X equals 0. 56g. 

The transmission of the entire system then becomes 29. 2% at 127X and 

25. 7% at 15X. Therefore, the decision has been made to apply the coating 

characteristics specified above. These coatings are part of the optical design 

given in Section 3.6.1. 

SPECIAL HANDLING 

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NRO APPROVED FOR 

RELEASE 1 JULY 2015 

:)i''E.CiAL HANDLING SECR - ET 

INTEROFFICE MEMORANDUM 

Date: 

Itek 

27 July 1967 

Page 1 of 2 Pages 

To: D. Shafer Facility: Lexington 

From: G. R. Wirtenson Facility: Lexington 

Subject: Coating Thruput Values (Project 9300) 

This report contains both theoretical and practical thruput values 

for the coatings specified. All values are given for 5600 X light. 

The theoretical data is obtained from our CDC 3300 computer using 

the MULTIFILM program. The practical data are measured values 

for the anti-reflecting films and estimates for the reflectors. 

The estimated values are based upon prior knowledge of typical 

performances. 

A brief description of the coating type is given. 

2-3) Folding Mirrors Internal-External 

Enhanced Aluminum (2 layer dielectric overcoat) 

Reflectance 

< of incidence Theoretical Practical 

45 o .9559 .93 

38° .9586 .93 

4-5) Pechan Prism Multi-layer dielectric Stack 

Reflectance 

Theoretical 

.9971 

< of incidence 

22.5 

Practical 

.985 

6) Anti-Reflecting Surfaces - 

< of incidence 

( 50 

Theoretical (15 

(25

o 

Deviation in transmittance 

Practical 

Magnesium Fluoride 

Transmittance 

Substrate index 

1.52 1.62 

.9874 .9935 

.9873 .9934 

.9868 .9929 

.0006 .0006 

.984 .988 

1.65 1.69 

.9949 .9964 

.9948 .9964 

.9943 .9958 

.0006 .0006 

.990 .993 

ADDENDUM 3. 6. 6-A 

SPECIAL HANDLING 
Itek 

-NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SPECIAL HANDLING 

INTEROFFICE MEMORANDUM 

Date: 27 July 1967 

Page 2 of 2 Pages 

To: D. Shafer Facility: Lexington 

From: G. R. Wirtenson Facility: Lexington 

Subject: Coating Thruput Values (Project 9300) 

As shown above, the expected change in transmittance per anti 

reflecting surface is of the order of 0.1% as angle of 

incident light changes from normal thru to 300 . A change of this 

order is not detectable by ordinary techniques and will not 

measurably affect system thruput. 

GRW/hb 

CC: R. Gebelein 

E. Hagerott 

F. Nitchie 

E. Prevost 

J. Rancourt 

S. Robinson 

SPECIAL HANDLING 

3.4-/e7 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SPECIAL HANDLING•. 

3.6.7 Optical Element Weights 

Introduction 

The weights of the optical components of the complete A/0 telescope 

are presented here, element by element, and the 

results are summed to give the total glass weight of 50.756 pounds. 

The window was assumed to be BK-7, 0.5 inches thick and 10.4 inches 

in diameter. The Pechan prism is 2.40 inches wide, to prevent vignetting at that 

element. One should note that the actual dimensions of the Pechan prism ((rather 

than its unfolded length) must be used when calculating its weight. The 

element diameters have been increased to allow for mounting so the weights given 

represent the weights of the actual elements. 

Table 3.6.7-1 is the lens specification data from which inputs to the weight analysis 

computer program were taken. 

Table 3.6.7-2 is a computer print out of the glass weights, except the window. In 

order to allow for mounting the elements, the actaul clear apertures have been 

increased. The resultant element diameters are larger than the clear apertures by 

0.4 inches for the window and objective lens, 0.26 inches for the power changer and 

field corrector, 0.16 inches for the zoom relay, and 0.10 inches for the eyepiece. 

The BK-7 window estimated weight is 3.856 lbs. The two (2) external CER-VIT 

mirrors will weigh 22.111 lbs. , and the internal CER -VIT folding mirror is 0.52 lbs. 

3. SPECIAL HANDLING SLORCT 
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SPECIAL HANDLING -SEeRETSummation: 

Total weight of glass elements, excluding the window 24. 269 lbs. 

BK-7 window 3. 856 lbs. 

Two (2) external mirrors 22. 111 lbs. 

Internal folding mirror 0. 520 lbs. 

Total weight of optical elements 50. 756 lbs. 

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WEIGHT ANALYSIS 

ID HIPOw 

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ELEMENT 

SPECIFIC 

GRAVITY 

BOUNDING 

SURFACES WEIGHT SUHWEIGHI 

3.610 1 2 8.942 EMS. 

Objective 

2 3.200 3 4 9.965 LBS. 

Power [4 7-3

3.610 

3.600 

5 

7 

6 

8 

.458 LHS. 

.207 LHS. 

Changer 

3.610 10 11 .399 LBS. 

3.600 12 13 .900 LBS. 

7 3.610 14 IS .682 LBS. 

Pechan 

Field 

Corrector 

pc 2.510 

2.510 

16 

18 

17 

19 

1.525 LBS. (Adjusted from unfolded weight, to actual, weight . ) 

79- .052 LBS. 

10 2.510 20 21 .034 LHS. 

11 3.610 22 23 .069 LBS. 

12 4.210 24 25 .139 LHS. 

13 3.610 25 26 .047 LHS. 

ZOOM WEIGHT OF CEMENTED ELEMENTS .186 LHS. 

14 2.510 21 28 .023 LHS. 

Relay 

15 3.600 29 30 .027 LBS. 

16 2.510 31 32 .013 LHS. 

17 3.600 33 34 .044 LBS. 

Table 3. 6. 7-2 

SPECIAL HANDLING SECRET 3.4- /13 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SPECIAL HANDLING —SEeFittle 3.600 35 36 .036 LBS. 

19 3.610 37 38 .041 LBS. 

2 0(Filter) 2.510 39 40 .022 Liis. 

21 2.510 41 42 .032 LBS. 

22 4.210 44 45 .135 LBS. 

23 3.610 45 46 .136 LBS. 

Eyepiece wF1GHT .OF CEMENTED ELEMENTS 

24 3.720 47 4A .118 LHS. 

25 3.610 48 49 .115 LBS. 

WEIGHT OF CEMENTED ELEMENTS 

26 3.610 50 51 .065 LBS. 

27 4.210 51 52 .042 LHS. 

WEIGHT OF CEMENTED ELEMENTS 

.271 LBS. 

.233 LHS. 

.107 LHS. 

TOTAL WEIGHT 24.269 POUNDS 

Table 3. 6. 7-2 (Continued) 

SPECIAL HANDLING 

3. e 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SPECIAL HANDLING 

3.6.8 Redesign of Power Changer 

The preliminary power changer design consisted of BK-7 and F-2 

elements. The lens specification data for this preliminary design up to the 

reticle is presented in Figure 3.6.8-1. Schematic diagrams of the power changer 

elements are presented in Figures 3.6.8-2, 3.6.8-3, 3.6.8-4. The transverse 

aberrations at the reticle of the low power objective system with this power 

changer design are presented in Figure 3.6.8-5 and the corresponding OPD 

(optical path difference) plots are presented in Figure 3.6.8-6. From 

Figures 3.6.8-5 and 3.6.8-6, it is seen that this design has approximately 

1/2 A of zonal spherical aberration. 

It was then decided to see if this zonal spherical aberration could 

be reduced by replacing the BK-7 elements with a higher index glass, namely 

SK-16. The lens specification data for this new and final design is presented 

in Figure 3.6.8-7. Schematic diagrams of the power changer elements are 

presented in Figures 3.6.8-8, 3.6.8-9, and 3.6.8-10. The transverse aberration 

plots and the corresponding OPD plots are presented in Figures 3.6.8-11 and 

3.6.8-12 respectively. From these figures, it is seen that the zonal spherical 

aberration has been considerably reduced. This power changer design was thus 

selected as the final design since a significant improvement in optical 

performance was achieved. 

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SFLL,IAL HANDLING --SE-G4T3. 6. 9 Interior Optical-Environmental Considerations 

Several thermo-optical analyses are being conducted in order to ensure 

optimum system performance. Dimensions that are critical to image quality are 

being developed to minimize the adverse influences of residual thermal soaks and 

shocks, axial and radial gradients, pressure shifts, dynamic loading, and thermally 

induced tube bending within the required temperature range. Although the specific 

effects of these loadings vary, in general, they consist of perturbations in thickness, 

airspaces, indicies of refraction of both lenses and the surrounding medium, radii 

of curvature, surface regularity, and structural geometry and shape, each of which 

may contribute to degraded performance. 

De-sensitization of image quality and position as a result of the environmental 

perturbations is being accomplished by combining materials which are dimensionally 

self-compensating when subjected to environmental changes. Improved performance, 

lower weight, and reduced cost are realized by using this technique rather than 

servo-mechanical provisions for refocus sing. 

The different environments anticipated during a mission occasionally suggest 

optical materials with conflicting response characteristics. In fact,in a single environment entirely different sets of materials are often required in order to control the 

various aberrations that are peculiar to all optical systems. The resultant trade-offs 

between materials is a problem in optimization which is being accomplished with the aid 

of Itek developed thermo-optical computer design programs. 

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The final rraterial selections will be made jointly by the structural, optical, 

and mechanical engineers on the basis of image quality, manufacturing tolerances, 

and thermal control requirements. 

The operating environment must be accurately known in three dimensions if the 

proper compensating materials are to be selected and the system made athermal. A 

heat balance analysis in which optical components hate been approximated by a series 

of nodes connected by conduction and direct and reflected radiation has produced the 

desired time-temperature histories. The analyses have included the effects of port 

cover and associated electronics, and have utilized additional Itek computer programs 

which calculate heat fluxes and vehicle temperatures as well as geometric and reflecting 

radiation view factors. 

Thermal analyses have indicated that on several elements (Ref. 3.7.6.2.3.1 

and 3.10.1.5.2.2.1) axial gradients are non-linear and that symmetric or nonrotationally symmetric radial gradients exist. These suggest either frame or finite 

element structural models to numerically predict deflected shapes. In all cases, 

support conditions have been and will be accurately simulated, and index gradients 

computed. 

A sufficient number of real rays is then traced to accurately predict resulting 

changes in optical path difference and RMS wavefront errors so that allowance can be 

made for the cascade of these local component effects with the perturbation of overall 

system growth, to obtain the total image quality degradation. The component effects 

available are discussed in Sections 3.7 to 3.10. 

It should be noted that rotationally symmetric and linear lateral (cf. Figure 3.6.9-1) 

isotherms produce defocussing and boresight errors respectively. Although either of 

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Figure 3. 6. 9-1. Linear Lateral Thermal Gradient, Temperature in °F 

For Use in Demonstration of Boresight Error. Solid Lines. 

Typical Thermal Perturbation in °F For 

Demonstration Purposes . Dotted Lines . 

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these can be important in photogrametric applications, their effects may be 

calibrated out without great difficulty (cf. Figure 3.6.9-2). Gradients which differ from 

either of these symmetries, however, have effects which are not easily eliminated (cf. Figures 

3.6.9-1 and 3.6.9-3) either mathematically or by a viewer in real time. Additionally, 

any distortion in the reseau will compound the calibration problem. For this reason 

every effort will be made to obtain symmetric loadings, and predicted isotherm 

shapes will be carefully evaluated. 

Several preliminary analyses of the proposed A 0 telescope system have been 

performed assuming four different cell materials and a uniform temperature soak of 

oF (i.

• o o 

-10 e. from 21.1 C to 15.6 C). 

The four cell materials chosen were steel (GC = 14.25 x 10

-6/

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C), aluminum 

(oC = 24.0 x 10-6/°C), beryllium (0c = 12.3 x 10-6/°C)and Invar (c,C = 1.5 x 10-6/°C) 

in order to evaluate a wide expansion coefficient range. Results are shown in Table 3.6.9-1 

It is apparent that the material selection must be carefully considered in order to 

minimize the aberrations. Although a sufficient number of analyses have not been 

performed to permit final selection (i. e. the most recent mounting techniques 

must be evaluated and several temperatures remain to be predicted), it is probable 

that aluminum is the best choice from a self-compensation point of view. 

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Table 3.6.9-2 indicates that even though the beryllium system is essentially 

compensated at both 70°F and 64°F, aluminum still has over four times the allowable 

temperature range, based upon uniform soaks and a 0.12 diopter object-reticle 

defocussing difference criterion. The possibility of selecting additional compensating 

materials for a predominantly beryllium system is presently unknown. A design 

study to determine the value of such an approach will be initiated. 

Table 3.6.9-3 indicates that the system must have both the reticle and eyepiece 

set out of focus prior to the mission to compensate for temperature changes. The 

required defocussings to compensate for pressure changes will be determined. 

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Changes in eye relief due to the imposition of the -10°F thermal soaks are 

in all cases less than 0. 1% and are, therefore, felt to be insignificant. 

The relative thermal sensitivities of the different elements in the AO 

telescope have been determined with and without refocussing on axis and at full 

field at both 127X and 31.75X magnifications. The ordinal representation of these 

values is presented in Table 3. 6.9-4, averaged over field position, and has been 

used both as a guide in determining areas of interest for thermal study and in 

checking the validity of extrapolating the effects of a temperature distribution on 

one component to other lens elements. The order was determined in part by 

weighting resultant 60PD' s caused by the curvature, thickness, and index changes 

which resulted from an imposed uniform temperature soak. 

3. - 1#0 SPECIAL HANDLING "-SfeRET-_- 
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TABLE 3.6.9-4 

Thermal Sensitivities of Optical Elements based upon AOPD' s caused by 

weighted curvature thickness and index change resulting from a uniform thermal soak. 

Values shown represent element numbers from most (top) to least (bottom) sensitive, 

as averaged over Field Height. 

Without Refocussing With Refocussing 

127X 31.75X 127X 

1 7 1 

2 3 2 

17 17 17 

9 4 25 

16 6 15 

15 25 16 

25 1 18 

29 16,15 19 

11 18 20 

18 8 28 

19 19 13,26 

20 20 10 

13 28 14 

26 26,13 24 

22 14 12 

28 10 29 

10 2 22 

24 24 27 

14 29 9 

12 22 11,21 

21 27 23 

27 12 

23 

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26 

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27 

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Thermally inducee bending of the telescope tube also degrades performance 

through the decentration and rotation of the optical elements. The 

deflected tube shape has recently been calculated for both an aluminum and a 

beryllium structure under conditions of end restraint which simulates both the 

case of a simply supported elbow at the shear mount and a fixed objective, and the 

case where both the shear mount and objective are assumed simply supported. (By using 

both support conditions, the actual shape will have been bracketed.) Temperature 

loadings in one system have not yet been defined due to a lack of information concerning 

the position of the tube with respect to bay electronics; however, several simple 4°F 

to 100F linear transverse gradients have been assumed in the interim in order to 

determine the order of magnitude of the resultant image degradation. The calculation 

and evaluation of this change in image quality is currently under investigation in both 

the 127X and 15. 88X systems. 

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$Pk.CIAI. 4-ANDLING. --6E6tRET• 

3.6.10 Effects of Window and Objective Pressure Differentials 

The performance of the A/0 optical system was evaluated for three 

pressure conditions on the window and element No. 1. 

The three pressure conditions considered are shown in Figure 3.6.10-1. 

3.6.10.1 Analytical Approach 

A structural analysis was accomplished to determine the 

deformation or sag of the optical elements due to the 

pressure intensities as shown in Figure 3.6.10-1. The 

resultant axial displacments of the surfaces at specific 

locations (nodal points) was expressed in a coordinateaxis system. 

A 10th order polynomial equation was fitted to the sag 

data over the clear aperture and study conducted on the 

CDC-3300 computer to evaluate the optical significance 

of the imposed pressure conditions on the performance of 

the A/0 system. 

3.6.10.2 Structural Evaluation 

The window configuration of BK-7 glass, 10.75 inches in 

diameter, and 0.5 inches thick was analyzed using the 

conventional two dimensional plate theory. The pressure 

was assumed to be acting on the 10 inch diameter clear 

aperture with the window mount configuration as shown in 

Drawing No. 115202. 

Three support conditions were evaluated, fixed edge, simply 

supported and supported on an elastic foundation (gasket 

and retaining flange). As one might surmise the clear 

aperture sag of the window supported on the elastic foundation is esentially the same as the simply supported condition. The main contribution of the elastic foundation is 

that of allowing about a 5 thousandth air gap change. 

The deflection curves for the 5.2 and 4.8 PSI pressure 

differential are shown in Figures 10.2.3-3 through 10.2.3-10 of the 

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analyses (Addendum 3.6.10-B). The data from these curves 

was transferred into tabular form and is presented in 

Table 3.6.10-7. It should be noted that the value of 

column 4, which is for a 15 PSI differential, was obtained 

by multiplying the value of column 2 by a factor of 2.88. 

The analysis of the objective element was done by Dr. Raab 

and is presented in Addendum 3.6.10-A. This lens was 

treated as a simple supported three dimensional elastic 

solid subjected to the three prescribed pressure intensities. A finite element method of analysis was used, 

together with a newly activated computer program for 

symmetric solids. 

Page 6 of the Addendum presents the output data of the 

axial and radial displacements. This data was 

converted into usable sag coordinates as shown in tables 

2.6.10-4 through 6. 

Tables 3.6.10-2 and -3 are the initial mode coordinates 

for Element No. 1. 

3.6.10.3 Optical Evaluation 

This analysis includes the change in index of the air with 

pressure as well as the physical shape of the surfaces. 

Of the three cases shown in Figure 3.6.10-1, the third, 

which is the worst case, was evaluated. The case is as 

follows: 

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Li ,P 0.0 P5-..r, 

The change in the optical path difference caused by the 

difference in the index of refraction of air in the spaces adjacent 

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to the window, and the de7Petttrow shape, is .001 

waves. This change in O.P,D. has no measurable effect 

on the nominal transfer function. 

Tne sag data of element No. 1,, for this case was fitted to a 10 order polynomial over the aperture. 

Surprisingly the 4th order term contributes .012 inches 

of sag over the clear aperture on the second surface while 

contributing only .0015 inches sag on the first surface. 

However, the fit was excellent on both surfaces across 

the areas used for this analysis. 

The 10.2 psi difference between the spaces on either 

side of the first element of the telescope objective 

causes that element to deflect in the manner described 

above. The new shape of the deflected element introduces approximately 1.0 waves of defocusing into the system 

and approximately 0.08 waves HMS of spherical aberration, 

while the change in field aberrations is neglibible (Fig. 

3 and 4). Thus the degradation is uniform across the field. 

Even assuming that the 1.0 waves of defocus are compensated by accommodation of the observer, or refocussing 

of the eyepiece, the image will still be degraded by the 

0.08 ENS of spherical aberration. The effects of this 

on the transfer function of the complete system at 127X 

are shown in Figure 5. 

If the area between the window and the objective lens is 

properly vented, only the window would experience a significant pressure load. 

The change in the optical path difference (OPD) at the 

final image of the A/0 telescope (with the nominal, flat 

window included) was calculated for this case, which is 

when the window has a 5.2 psi pressure differential and 

an elastic support. 

The change in the OPD at the final image in the 127X mode 

due to the window shift and deflection was calculated on 

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11 1 LI r r 

axis and at full field, and was found to be less than 

0.001 waves in both cases. This change is negligible and 

would have no measurable effect on the resolution performance of the A/0 telescope. 

In conclusion, even though the window deflections for all 

cases considered do not have a discernible effect on the 

nominal transfer function, a 10.2 psi difference across 

the front element of the objective causes 0.08 waves RMS 

degradation at 127X after defocussing which is intolerable. 

If required, a 10 psi difference across the front element 

could be tolerated from the image quality standpoint 

under severe conditions but the system should not be 

designed nominally this way. A 0.4 psi difference across 

the first element would have no discernible effect on the 

nominal transfer function. 

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Itek Abbet4 1)‘)," 3.‘.(0 - A 

C5 July 1967 

Page 1 of 1 Pages 

To: G. Lenertz Facility: Burlington 9 

From: A. R. Raab Facility: Burlington 10 

Subject: Lens Element No. 1 of Project 9300.47M 

Attached are the summarized results of my analysis of the deformations 

of Lens Element No. 1 when it is subjected to the pressure loadings that you 

specified. 

Page 2 indicates the finite element subdivision and the relative positions 

of the nodes. Also given is a table of the pressure intensities for the three 

loading conditions. Pages 3 through 5 show the axial displacements of the surface 

1-46 due to each loading condition. Page 6 contains a tabular listing of the axial 

and radial displacements of all nodes for each loading condition. 

This lens has been treated as a three dimensional elastic solid subjected 

to surface pressures. The finite element method of analysis has been used, together 

with a newly activated computer program designed to treat axi-symmetric solids. 

It is interesting to note that the results for Cases 1 and 2 do not 

exhibit merely the reversal of the pressure differential, as would have been the 

case if a two dimensional analysis had been used. Instead we find that the 

maximum surface displacement is 15.08 micro-inches for Case 1 and -18.57 microinches.for Case 2. As I indicated previously, this is due to the different radii 

of curvature of the two surfaces, as well as to local compression of the material 

near each surface. 

Also of interest is thelfact that the results for Case 3 differ from 

those to be expected from a scaling of Case 1 to produce a pressure differential 

of 10.2 psi. This scaling factor (25.5) would be applied to all load values, and 

consequently to all displacements, associated with Case 1. The displacement of 

surface 1-46 determined in this manner is shown as the broken line on Page 5. 

The maximum surface displacement would then be 384.52 micro-inches instead of the 

value of 421.00-'micro-inches evaluated in Case 3. 

A. R. Raab 

/pb 

cc: W. P. Barnes, Jr. 

R. Carignan 

A. Van Sickel 

M. Kahan 

S. Robinson 

A. Wright 

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BY: GEORGE LENERTZ 

DEPT: F DATE: 3/A-mr 

TITLE: 

9303 OPTICAL SYSTEM 

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DEPT:F 5 40 DATE: -3/A/4r 

TITLE: 

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PAGE: 1e...?..?-sePROJECT: ..-‘'42'9'" 

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3. 6. 11 Lab Module Atmosphere Effects on Optical Design 

In section 3.6.9 the effects of pressure changes from air at STP to air 5.0 psi 

are discussed. Table 3. 6.9-3 indicates a focal shift of -3.81 diopters. 

This sections shows the effects of changing from air to an environment of 

a 30% He/70% 02 mix (by voitunoat STP. Table 3. 6. 11-1 shows the results of our 

analysis. 

As indicated in the footnote of Table 3. 6. 11-1, the effect of reducing the 

pressure to 5.0 psi would be 33% of the focal shift at STP. 

To sum up the final focal shift between the object and the reticle for the change 

from air at STP to 30% He/70% 02at 5.0 psi, we use the values of both Table 3. 6.9-3 

and Table 3. 6. 11-1. 

Focal Shift due to 5. 0 psi -3. 81 D 

33% of focal shift due to 30% He/70%02 -0.07 D 

Total focal shift - 3.88 D - -- 

The defocussing required to compensate for the environment is built into the 

telescope at assembly. Performance tests are conducted by defocussing the test 

collimator to compensate for the laboratory environment. 

SPECIAL HANDLING 

3.6-199 
Effectsof a Shift fromAirEnvironment toa30% He, 

Standard Convention,Nominal SysteminFocus 

Defocussingof both Reticleand Object Expressed in Diopters 

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-Stefit-T-- 

3.6.12 Relationship between Field Curvature and Off-axis Performance 

This report discusses the effects of various balancings of the astigmatic 

field curves of the AO Telescope upon best focus image quality and also the 

accommodation required of the eye to reach this best focus. 

3.6.12.1 Introduction 

The Optical Design Department at Itek has completed a trade-off study to 

determine the effect of various balancings of the astigmatic field curves upon 

best-focus image quality, and also the accommodation required of the eye to 

reach this best focus. The data resulting from this study is based upon thirdorder aberration theory and assumes a 2 mm exit pupil diameter for the AO 

telescope. 

3.6.12.2 Discussion 

The mean astigmatic field curve is defined as the locus of points midway 

between the tangential and sagittal astigmatic field curves. In third-order aberration 

theory, if astigmatism is the predominant off-axis aberration present, the mean 

astigmatic field curve will also be the curve of best focus. 

The angular resolution in minutes of arc observed at the eye has been calculated 

for various mean astigmatic field curves which correspond to various balancings of 

the tangential and sagittal field curves. It is assumed here that the eye accommodates 

to this mean astigmatic curve. This data is presented in Figure 3.6.12-1. The 

deviation of the mean astigmatic field curve from a flat image plane at a half-field 

angle of 30 degrees is expressed in diopters and is labeled DBmax. 

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In t;.e AC design, the mean astigmatic field curve has a value of 2.0 diopters. 

As can be seen from Figure 3.6.12-1, the design case of DBmax. = 2.0 diopters 

represents a good balance between resolution across the field and the amount of eye 

accommodation required to reach best focus. It is, therefore, apparent that the 

off-axis resolution of the telescope can be improved only at the expense of a larger 

required eye accommodation. 

Because of higher order astigmatism (6th,7th, etc.) and also the presence of 

other aberrations, the best focal positions at any field angle will not, in general, lie 

midway between the tangential and sagittal astigmatic field curves. In the telescope 

design, the best focus is at 1.5 diopters at full field, and the modulation transfer 

function curves give resolutions better than that predicted by the DB 

max. = 2.0 

curve in Figure 3.6.12. -1. Thus the model we have been using is a good but 

slightly pessimistic one for this specific design. 

3.6.12.3 Comparison of Theoretical Analysis with Actual Performance 

The mean astigmatic field curve has a value of 2.0 diopters nt 127X. However, 

because of higher order aberrations, the best focus lies at a position of 1.5 diopters 

at full field. The effects of higher order aberrations vary greatly and are beyond the scope 

of the preceding analysis. However, by comparing the actual performance with that 

predicted by the preceding theoretical analysis, it can be shown that a fair agreement 

has been achieved. The improved performance of the optical design comparison to the 

theoretical model is due to the optimum state of the actual design. 

The ground resolution at best focus over the 60 degree apparent field of the 

telescope at 127X is presented in Figure 3.6.12-2. This data is based on the current 

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normalization of the Schade threshold, and a distance of 80 nautical miles at nadir. 

From Figure 3.6.12. -2, it is seen that the nominal system under the stated 

conditions resolves 2.8 feet on axis and 10.4 feet at full field at best focus (1. 5D at 

full field) at 127X and 80 nautical miles; these values correspond to angular resolutions 

(observed at the eye) of 2.4 and 9.1 minutes, respectively. This value represents 

the static resolution of the optics alone, and should not be interpreted as a prediction 

of operational system performance, in which other degrading factors must be included. 

The theoretical analysis, as presented in Figure 3.6.12-1, predicts an angular 

resolution of 14 minutes at full-field for a 2.0 D position. In conclusion, it is felt 

that this agreement is close and that the data in Figure 3.6.12-1 is valid. 
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,4 
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3. 6.13 Zoom Lens Type Tradeoff 

The optical design tradeoffs between mechanically and optically compensated 

zoom configurations for the A/O telescope are discussed in this section. 

The three major zoom lens types are: 

1. Mechanical Compensation - two or more lens groups move with 

respect to the focal plane and each other. 

2. Linear Compensation - A mechanically compensated lens with the 

added restriction that the motions of the moving groups are linearly 

related. 

3. Optical Compensation - A linearly compensated lens with the added 

restriction that the moving groups move as a unit with one stationary 

group between each pair of moving groups. 

Thus, optically compensated lenses comprise an extremely 'small subset 

of mechanically compensated zoom lenses. The reason that they are used is based on 

mechanical considerations when they provide satisfactory performance. The 

mechanical tradeoff is not straight forward since in certain mechanically compensated 

lenses (e. g. , AO telescope) only two groups move with no stationary elements in between; 

whereas,;in all optically compensated lenses two or more groups move with mechanical 

means required to keep a lens group stationary between each pair of moving groups. 

In addition, the defocussing as a function of zoom position is exactly zero for 

mechanically compensated zoom lenses but is a non-zero value for optically compensated 

zoom lenses reaching small values as the number of moving groups is increased. 

The practical question arises of whether two conjugate pairs (in this case the objectimage pair and the entrance pupil-exit pupil pair) can be kept stationary in an optically 

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compensated zoom. This has been shbsn to be possible paraxially by Silvertooth in a 

J. O.S. A. article and is thus clearly achievable with mechanically compensated lenses. 

However, the ability to control the real exit pupil position to ± 0. 02 inches over a 2:1 

zoom range and 60 degree apparent field is not as easily proven and in fact is a property 

of the higher order aspects of the design. No optically compensated or mechanically 

compensated lens in the open literature has been found with these properties. For 

this and othe r reasons, the A/0 telescope zoom lens was designed to achieve these 

specifications without the added restriction of optical compensation. The resulting 

zoom relay-eyepiece configuration has less than 0. 2 waves spherical aberration and 

chromatic aberration throughout the zoom on axis. The variation of field aberrations 

with zoom is very small and the actual field correction is limited by the eyepiece 

portion rather than the zoom portion of the system. 

Wooters and Silvertooth, J. 0. S.A. 55, 347 (1965) 

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3.6.14 Effect of Melt Deviations 

Introduction 

The effect of the standard melt tolerance of 1::1.001 of the nd value and ICI. 8% 

of the Vd value for the objective lens elements on the performance of the 9300 

objective lens system has been investigated in the 127X mode of operation. This 

mode was chosen since this is the magnification at which the resolution requirement 

is to be met. 

Cases Investigated 

The first case investigated was that in which the indices at all wavelengths for 

both the SK-16 positive element and the KzFSN-4 negative element was raised by 0.001. 

The second case for both elements were lowered by 0.001. In both of these cases, the 

effect of the change of indices on image quality was negligible. However, the back 

focus decreased by 0.1 inch in the first case and increased by 0.1 inch in the second 

case. The nominal back focal length is 0.9 inch. These two cases indicate that serious 

losses in resolution can be avoided by proper matching of indices, i. e. , an SK-16 

element whose index is +0.001 from nominal should be used with a KzFSN-4 element 

whose index is approximately +0.001 from nominal, etc. 

For worse cases, the indices of the crown and flint elements were changed 

by 0.001 in opposite directions. This produced approximately 2 waves of spherical 

aberration and changed the back focal length by 0.75 inch. The spherical aberration can 

be eliminated by changing the airspace between the objective elements by ±0. 02 inch 

depending on the case. The back focal length, however, cannot be restored to its 

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nominal value in all cases even with the aid of element thickness adjustment. Other 

first-order quantities such as equivalent focal length and Gauss image height can be 

held within 1%. 

It is, therefore, felt that SK-16 and KzFSN-4 glasses can be ordered with the 

standard melt tolerance of ±0.001 for ndand ±0.8% for Vd 

only if the mechanical 

adjustments shown in Figure 1 can be provided. Similar adjustments should also be 

provided if a melt tolerance of ±0.0002 is ordered but they could be on the order of 

one fifth those shown in the Figure 3. 6. 14. 1. 

3. 6-Z49 
SPECIAL .........LING -SE-CAE-7 

Whey 00i -4 x ..:0 

2 ia, N fe + 

A le -1 

W

0.• 

Z IL in 

le a vi 0 V 0. 

1:3=nr:ft 

0 

+i 

IL 

X\ 

U 

0 

Figure 3.6.14-1 

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3.6.15 Window Thermal Analysis 

There are several distinct constraints which the window must satisfy if it is 

to contribute to optimum system imagery. Unfortunately, many of these constraints 

are incompatible when considered together with the properties of commercially 

produced astronomical quality glass. The resultant trade-off required to select the 

optimum glass type is multi-dimensional and must encompass every parameter from 

weight to radiation-produced dispersion changes. Of critical importance are the 

changes in shape and index imposed by uniform temperature soaks, and both axial 

and radial thermal gradients. Axial gradients have as a critical parameter the 

linear thermal expansion coefficient while radial gradients must be additionally 

weighted by the thermal coefficient of the refractive index, as indicated in Table 

3. 6. 15-4b. (The effect of LsN/6T is not felt with axial gradients as it represents a 

uniform change over the entire window' s wavefront. ) Thus, the type of gradient 

expected can be all important in selecting an optimum material, and this is especially 

the case when, as in BK-7 vs. fused silica (cf. Table 3.6. 15-1), both d and dN/dT 

vary widely. Thermal boundary conditions are not well defined, but regardless a 

preliminary attempt was made at material selection. 

The effects of linear axial gradients and uniform soaks are discussed in Table 

3.6.15-2 and are shown not to modify image quality. Assuming a parabolic set of 

isotherms for a radial gradient, the maximum peak to peak tolerable temperature 

variations are presented in Table 3.6.15-3. For a 0. 5-inch thick window, temperatures 

must be controlled to 2.0 degrees for fused silica but only to 4.6 degrees for BK-7 

(on-axis-high power). More recent information on the thermal boundary conditions 

has been generated and it is expected that these isotherms will be of additional help 

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in the selection of an optimum material. An Itek developed, Fermat' a Principle. 

Ray Trace program will be used to analyze the window in the manner described for 

analyzing the objective lens (cf. Section 3.10.1. 5. 2.), and the results interpretted 

with respect to material type. 

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TABLE 3.6.15-1 3.6.15-1 

Selection of Optimum Window Material 

Design Data 

Parameter BK 7 Fused Silica 

BTU 6437 . 7768 

. 170 

0.59 x 10-6 

Thermal Conductivity, K, F T 

B Specific Heat, C, —

TU

o--- 

HR F . 

. 205 

-1 7.7 x 10-6 

p # F 

Expansion Coefficient, cC , 

dn/dt (Absolute)(d/He/5876R) 0.9 x 10-6 10. x 10-6 

Youngs Modulus, E, psi 11.822 x 10 6 10.5 x 10 6 

Poissons Ratio, IL . 208 . 170 

Density, p 2.510 2.202 

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TABLE 3.6.15-2 

Selection of Optimum Window Material 

Environmental Effects 

Load Type BK-7 Fused Silica 

5.2 psi Pressure on Circular Simply- . 0021" . 0031" 

Supported Window gives maximum 

deflection of: 

(Added here for constant' s effect on power only 

Actual pressure deflected shapes have been 

analyzed separately.) 

10o F (typical) uniform axial gradient 

through window gives maximum deflection of: . 0012" . 0001" 

* * 

. 0033" . 0032" 

Figure changes and index shifts due to uniform thermal soaks have no effect upon image 

quality. Index shifts due to uniform axial gradients also have no effect, as allowable 

AN> . 001 for window with slight power - (X /20 maximum A OPD over field/criterion) 

* . 0033" ± Sags < . 1378" allowable sag (same X /20 criterion) 

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TABLE 3.6.15-3 

Non-rotationally Symmetric Radial Gradients 

Allowable peak to peak variations in radial temperture distribution (°F) based upon 

X /13 RMS tolerable and typical parabolic gradient shape on window. 

On axis-high power. Note that Gradient Shape is actually a function of window thickness, 

and that equation b in Table VIII is non-linear into , given a non-zero power. 

Window Thickness (inches) BK-7 Fused Silica 

0.25 9.16 3.06 

0.50 4.58 1.96 

0.75 3.42 1.47 

1.00 2.32 1.16 

Typical expected value must yet be fully determined. 0. 50" thickness desirable 

from pressure test point of view and fabrication. Therefore 1/2'' non-browning BK-7 

seems at present thermo-optically more desirable than Fused Silica. However, as many 

other trade-offs are involved (e. g. , there is an additional 0.5 pound per window with 

BK-7) and as the shape of the temperature distribution is quite important, optimum 

choice cannot yet be definitely determined. 

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TABLE 3.6.15-4 

SOME CALCULATION FORMULAE, DERIVED 

Maximum Deflection, It (Pressure) - 3W(M - 1)(5M + 1) a

2 

16 7r EM

2

t

o

3 

where W = p a

2 M = 162 and p = density, a = plate radius, tt = Poisson' s 

ratio, E = Youngs modulus and t

o 

= plate thickness 

b. 60PD (N - 1) 

1-C (x2 

2 

+ y

2

) 

+ t

o

oc T + 

1 +

C oc T 

+t

o 

6N 

6T 1 + - C2 (x2 

+ y

2

)

1 

where 60PD = change in optical path difference due to temperature, C is 

an effective curvature (used to introduce approximate amounts of 

power), x and y are radius coordinates, N = index of refraction, 

= thermal expansion coefficient, 6 T = new temperature less 

nominal, and 6 N = thermal coefficient of the refractive index. 

6 T 

c. RMS (AOPD)

2 

where RMS = root mean square wavefront deformation 

Ji Lif Li NG 

T - C (x2 

 + y

2

)