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Document No. 50301-122-1 

Copy No. of 40 copies 

No. of Pages 380 

MINUTES 

OF 

INCREMENTAL PRELIMINARY DESIGN REVIEW. 

OF 

ACQUISITION SUBSYSTEM. 

OF 

GE-AVE CEI-010AI 

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SUBJECT: Minutes - Incremental Preliminary Design Review 

of the Acquisition Subsystem of CEI MOL 010AI. 

REFERENCES: a) Statement of Work Contract AF 18(600)-2955 

CONTENTS 

1.0 Purpose 

2.0 Results 

2.1 Summary 

2.2 Action Items 

2.3 Post-PDR Action Items 

3.0 Discussion 

3.1 Time/Place 

3.2 Attendees 

3.3 Comments 

4.0 Agenda 

5.0 AF/AS Questions 

6.0 Minutes of Side Meetings 

6.1 Optical 

6.2 Thermal 

6.3 Mechanical 

7.0 Presentation 

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1.0 Purpose 

To conduct an Incremental Preliminary Design Review (PDR) 

of the Acquisition Subsystem of CEI MOL 010AI of 

Specification CP 1000AI. 

2.0 Results 

2.1 This incremental PDR was satisfactorily completed. 

General Electric agreed to provide completion dates 

for the action items with the formal minutes, which are 

provided below: 

2.2 l're-PDR Action Items 

None 

2.3 Post-PDR Action Items 

2.3.1 GE will analyze and optimize the backup mode using the 

inverse of the curve shown in Figure (1) and the additional 

constraint that the optimum performance is desired for 

angles from nadir to +50 degrees. Action to be completed 

by 4/19/68. 

0 Pit 

• -2 SLOPE 

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2.3.2 GE to provide impact on system reliability program costs, 

weight and power by deleting the back-up capability, etc. 

Action to be completed by 4/19/68. 

2.3.3 Propose changes to para. 3.1.2.1 (d&e) to CP 1000AI to 

consider effectiveness relative to target selection. 

GE will determine the reliability/effectiveness, determine what changes can be made (without redesign) to 

increase the number by considering: 

A. Better estimates of component performance 

B. On-orbit maintenance 

C. Considering only mission critical items 

D. Degraded modes of operation 

Action to be completed by 5/6/68 

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2.3.4 AF/AS to consider revision of Para. 3.1.2.1 of CP 1000AI 

to reflect use of ATS operation. 

2.3.5 Determine impact of extended door-open times on: 

A. Scanner temperature gradient 

B. Operational temperatures on roll & pitch gyros. 

Action to be completed by 5/6/68 

2.3.6 GE shall submit a recommended program to AF/AS over 

and above the AEDC plume test to define the contamination 

problem for the Alpha Subsystem. Action to be completed 

by 4-26-68 

2.3.7 AF/AS'oovide presently available definitio of a 

pres.x.17ed gloved hand. 

2.3.8 AF/AS to provide photographic procedure for processing 

3404 type emulsion on base film to obtain spatial frequencies provided on a standard Air Force resolving 

target per MIL-STD 150A with 6:1 contrast ratio. 

2.3.9 GE will review and refine the data proposed as to 

spectral reflection eye hazard potential to the crewman when using the ATS system. In particular 2% reflectance from water should be used in computing answers. 

Spectral cut-offs provided by the lens-coatings combination of the proposed systems should be included in the 

analyses. Action to be completed 4-26-68. 

2.3.10 GE will review the cue pre-pass briefing procedure with 

the objective of: 

A. Eliminating or simplifying the four-step procedure 

B. Minimize power requirements 

C. Minimize hardware impact and submit recommendation 

to AF/AS. Action to be completed 4-19-68. 

2.3.11 GE will submit to AF/AS an interim report on the jitter 

test planned at Subcontractor A. Action to be completed 

5-3-68. 

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GE to transmit to AF/AS the Advanced boresighting analysis, 

including definition of simultaneity required on VO & ATS 

buttons. Action to be completed by 5-13-68. 

2.3.13 

2.3.14 

2.3.15 

2.3.16 

3.0 

GE to submit updated set of Subcontractor A drawings 

to AS. Action to be completed by 4-19-68. 

GE to prepare an analysis which will show the amount of 

focus adjustment required after insertion of a new film 

module. Action to be completed, 5-31-68 (Preliwinary), 

6-17-68 (Demonstration), 7-12-68 (Final). 

GE to send TWX to AF/AS giving results of trade study 

incorporating Be in the film module and VDP. Action to 

be completed by 6-17-68. 

GE will report to the Air Force the size (angular) of the 

peripheral display lights in the present Itek design. 

Action to be completed by 4-19-68. 

Discussion 

3.1 Time and Place - The meeting was held at Radnor, Pa., 

on March 6, 7 and 

Attendees 

8, 1968. 

General Electric 

J. McGuckin 

W. T. Jones E. Siegrist 

W. Nicholini E. H. Reese 

R. J. Barchet G. R. Christopher 

C. J. Galen F. Nistico 

G. P. O'Brien B. L. Bailey 

D. M. Smith L. Petkofsky 

R. A. Englund R. J. Boram 

W. J. Manley D. C. Marr 

C. T. Boman M. L. Peterson 

P. Feig D. Ungvarsky 

W. R. Guard W. Montgomery 

R. B. Phillips M. A. Payonk 

L. D. Taylor J. H. Frey 

P. J. Ferrara B. Bresnick 

F. B. Woestemeyer J. M. Denshaw 

E. H. Ernst M. H. Peters 

G. Stocking R. E. Roney 

V. Reis R. T. Kern 

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Aerospace 

D. E. Whelan 

L. L. Thomas 

H. L. Ferger 

D. Nicholson 

F. W. Belina 

B. Siegel 

L. C. Lidstrom 

R. H. Leatherman 

J. E. Bennett 

W. C. Crooker 

W. P. Denson 

H. Apoian 

P. Dahl 

T. A. Hussman, Jr. 

D. Griep 

R. F. Gehrke 

Air Force 

Maj. F. Neubeck 

Lt. Col. N. J. Farrell 

Lt. B. A. Knight 

Maj. H. W. Hartsfield, Jr. 

Maj. F. F. Doppelt 

3.3 Columen.ts 

3.3.1 GE states that the modulation at the film plane theoretically will not exceed 15% due to Newton's rings. LSI 

has assured GE that the solenoid can be adjusted such 

that the film gate pressure will not cause Newton Rings. 

3.3.2 The thermal effects of firing the hi-thrustor for 1500 

sec, for orbit adjust, was discussed. There is a minimal 

effect on peak shroud and insulation temperatures, however, 

the effect of degradation of the thermal control coatings 

due to thrustor exhaust products must be evaluated by 

tests. 

3.3.3 GE will work with the Air Force to define a limited 

search mode which is consistant with the capability 

of the baseline design and mission objectives. 

3.3.4 

3.3.5 

3.3.6 

GE will continue to study need for relaxing decoupling 

requirement. 

GE will submit a report on telemetry capability associated 

with the Acquisition Subsystem. 

GE to review film qualification at 15 PSI with 100% 

oxygen for possible test relief. 

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3.3.7 TBD items in specification, i.e., off-axis performance, 

etc. must be completed prior to completion of PDR. 

3.3.8 Prior to completion of PDR updated subcontractor 

specifications and film module specification shall be 

submitted to AF/AS. 

/s/ J. McGuckin /s/ N.J. Farrell L/Col. /s/ D. E. Whelan 

General Electric Co. Air Force Aerospace 

The actions and comments contained in these minutes are certified 

to be a true copy of those recorded and signed in rough draft form 

at the PDR meeting. 

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ACQUISITION SUBSYSTEM 

AGENDA 

NO. PDR AGENDA ITEM 

1.0 REQUIREMENTS (Q#2,15,61,62)* 

SPDR 

CEI 

2.0 INTERFACES 

3.0 DESIGN CONCEPTS 

3.1 Introduction - S/S Description 

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3.1.1 

3.1.2 

3.1.3 

3.1.4 

3.1.4.1 

3.1.4.2 

3.1.4.3 

3.2 

3.2.1 

3.2.2 

Functional Description 

(first level breakdown) 

Power Tabulation (Q#57)* 

Weight Tabulation 

Critical Subsystem Analysis 

Jitter Performance (Q#8)* 

Slew Performance 

Unbalance Effects (Q#59)* 

Acquisition Optics Assembly 

S/C A Action Items (Status/Resolution) 

ATS Optics Analysis 

(Q52, 53, 20, 17, 4, 5, 18, 19, 21, 22)** 

3.2.3 ATS Optics/Vibration Analysis 

(012)* 

3.2.4 ATS Controls Analysis (Q#26,27,28, 

29,30,31)* 

3.2.5 Bearings (Aft, Fwd, Cross-Roll) 

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3.2.6 ATS Thermal Analysis (Q#38, 39, 40)* 

3.2.7 ATS Structure Analysis 

Weight (043,55)* 

3.2.8 Boresighting 

3.2.9 ATS Error Analysis (Side Meeting) 

(Q#60)* 

3.2.10 Image Derotation 

3.2.11 Eye Hazards/Blanking (Q#33,34,35)* 

3.3 VDP Action Items (Status/Resolution) 

(06,14,63,64,65)* 

3.3.1 Optical Analysis (Q#7,36,37)* 

3.3.2 Film Module 

3.4 Drive K Electronics 

3.4.1 Requirements 

3.4.2 Functional Description (2nd level) 

3.4.2.1 Schematics/Block Diagrams 

3.4.3 Weight and Power by Function (@#41,42)* 

3.4.4 AF/AS Questions (#23,24,25,32,58)* 

3.4.5 EMI Design (Q#10)* 

3.4.6 Thermal Design 

3.4.7 Interfaces 

3.4.7.1 Command 

3.4.7.2 Acquisition Optics 

3.4.7.3 Mounting 

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3.5 Human Factors 

3.5.1 General Approach (Restraints) 

(Q#51,66,49)* 

3.5.2 Headrest 

3.5.3 Consoles 

3.5.3.1 D. Panel Layout 

3.5.3.2 C Panel Layout 

3.5.3.3 Film Module Storage 

3.6 L. H. Control Stick 

(Questions Only) 

3.7 Gyros (09,11)* 

3.8 Subsystem Consideration 

3.8.1 Reliability/Safety 

3.8.2 Maintainability 

4.0 UNSOLVED AREAS 

4.1 Inconsistency in Requirements 

4.1.1 Proposed Changes (Q#54)* 

4.2 Areas of High Risk 

4.3 Problems and Recommended Solutions 

4.4 Shroud Design (Q#44,45,46)* 

5.0 DEVELOPMENT PLAN 

5.1 Development Schedule 

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5.2 Mockups/Breadboards/Brassboards 

5.3 Development Test Plan 

*Refers to questions answered during the course of the presentation. 

** Written answers to questions included in minutes. 

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AF/AS Questions Based Upon Pre-PDR Documentation Submittal 

NOTE: All questions were answered satisfactorily during the 

course of the PDR presentations. AF/AS reviewed the 

questions during a caucus on the second day of the PDR 

and asked for additional information on several questions, 

which was provided. The point in the PDR where the 

submitted questions were answered is indicated on the agenda. 

1. How does computer accept updating information? 

2. Two minute accuracy with MCS corrections - is it independent 

of magnification? 

3. What is the impact of incorporating the Alpha Numerics into 

the Acquisition Optics? 

4. Page 2-76: They are questioning the correctness of the 

mathematics (706.5 - 708) 

5. What the the effects on the adjustments on the r ticle of the 

Acquisition Optics? 

6. GE to conduct a trade study to find the advantages and disadvantages of projecting the light through the film base. 

7. Will placing the film against the prism cause Newtonian 

rings - How do we plan to avoid this problem? 

8. Subcontractor A controls - explain. Customer desires a general 

discussion to determine if characteristics of encoders, torque 

motors, etc. are meeting GE error allocation. 

9. In the Honeywell PDR package a statement is made: "Lab 

experiments show that this is the lowest noise configuration" -

please explain. Aerospace considers this a very grandiose 

statement. Noise performance exceeds GE spec - please explain. 

10. Drive A Electronics treated effects of EMI on•performance -

why was a similar discussion not included in Drive K Electronics, 

particularly with reference to jitter and smear. 

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11. In the Honeywell documentatiOn the statement was made that the 

hold down clamp was torqued to 100 inch ounces. Is this an 

error? If correct, please discuss. 

12. ATS Optics/Vibration Analyses - Aerospace considers there is 

a lot of work remaining to be accomplished -- discuss the 

future activities planned for this area (jitter test) 

13. EAR report page 2-69/2-70: Please update our vignetting study 

and including obscuration. 

14. Paragraph 1.2.5 - VDP - Frame retrieval time--GE states that 

we meet the frame retrieval time because we have numbered 

the frames consecutively. Can GE really meet the Spec? -

Please discuss. 

GE Comment: Please make the point that we have gone to the 

octal system which permits us to number the 

frames consecutively. If the film supplier 

numbers the frames consecutively, GE will meet 

the Spec. 

15. Is the first stick to go into the visual optics range the 

controlling stick? Is the right hand stick still controlled 

by the magnification stick when you are in the main optics? 

16. Summarize human engineering studies, either simulations 

or analysis on peripheral display. For example, with FOVEA 

at center of eye-piece field of view, what must characteristics 

of peripheral display be in order to be "seen" by the peripheral 

visual sensors as functions of various variables (soon as scene 

brightness, brightness of peripheral display lights, size of 

peripheral display lights in angular subtense at the eye, 

color of peripheral display lights, etc.) How does preliminary design stack-up against such criteria? 

17. What the focus characteristics of the peripheral display 

lights relative to the scene? 

18. Are CE/SUB following up on these recommendations? (Para. 2.1.2.3, 

Re: Optical Design). When will results be known? (Tolerances 

on curvature Radii; triplet instead of doublet objective). 

19. The results contained in table 21-3 indicate definite need for 

corrective action. Resolution provided is in some cases worse 

than using a window. 

20. Comment: GE analysis makes some approximations which may not 

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be valid for this design. Conclusions and recommendations 

might be different if better model was used. 

21. What about the field curvature-off-axes resolution trade-off? 

No consideration was given in EAR on tilting the decentering 

tolerances. What is effect on performance? 

22. Discuss tests which will be used to verify optical performance 

of the flight hardware. 

DIGITAL PROCESSOR: 

23. What is the magnitude of the drift caused by integrating the 

least significant bit of the rate command at 19.5 KHz? 

24. Does the least significant bit of the rate command in the 

digital processor correspond to the least significant bit of 

the rate c mmand that is generated by the software? 

25. The number of bits that is required in view of the above 

does not seem compatible with the 16-bit(?) word that is 

transmitted from the computer to the digital processor. 

JITTER DUE TO ENCODER BIT-TO-BIT ERROR: 

26. What is the PSD from the bit-to-bit error on the 18-bit 

encoder as you now see it? How does this compare to the 

requirement given in the EAR? 

27. Does the 19-bit encoder which has the same package size as 

the 18-bit encoder have one more natural bit, or does it 

extrapolate one more bit? 

PSD Analysis: 

28. Justify the "2" or lack of it for: 

(a) Your bearing PSD program 

(b) Honeywell's gyro PSD data 

(c) Your encoder noise analysis 

29. Page 2-96 - How was low frequency of 0.9 RAD/SE cut-off for 

bearing noise obtained? The Bearing Model does not seem to 

be derived from the main drive model, what is the basis for 

the bearing model? 

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30. Pages 2-138 and 2-144 - Figure 2.2.25 does not appear to be 

the correct figure for data described on references pages. 

Please clarify. 

31. Verify selection of brushless torquer. 

32. Provide and discuss the mechanization of the D/A conversion 

in the digital processor. 

SOLAR BLANKING SHUTTER 

33. Can it be made to operate against specular reflections discussed 

in eye-hazards study? 

34. Can it be made to operate when laser beam impinges? What will 

color characteristics of sensor be? 

35. Where is shutter reset mechanism located? How long required 

to manually reset it? 

VDP 

36. No off-axis optical analysis provided. 

37. Analysis does not include optical data length through film 

base. In previous discussions in which justification for 

projecting image through base, it was stated that this different 

optical path was accounted for in the analysis. The off-axis 

rays could be affected by this omission. 

THERMAL ANALYSIS 

38. Trade-offs provided in EAR are satisfactory. Would like to 

have preliminary thermal design for selected hardware, design, 

particularly for the equipment mounted externally from the LM. 

39. What are results in terms of optical performance of the 

selected thermal design? 

40. What thermal problem areas are still under study? 

WEIGHT 

41. Paragraph 1.2.7 and 4.4.1 - What is weight status of Drive K 

Electronics? How does it compare with weights negotiated in 

October? 

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42. In 4.4.1 there must ue a TYPO. Drive K have always weighed more 

than 3.5 lbs. 

43. Table 4.4.1 should be updated. Believe weight is closer to 

330 lbs than to 375 lbs. 

SHROUD DESIGN: 

44. Would like discussion in detail of the new shroud design. 

45. Is its design compatible with the vignetting analysis provided in the EAR? What are the vignetting characteristics? 

46. What are out-gassing characteristics of fiber-glass shroud 

and what is impact on optical performance? 

LAUNCH LOCKS: 

47. Discuss launch-lock characteristics. Where used? Reliability, 

etc.? 

ALIGNMENT 

48. Discuss features permitting optical alignment of various elements 

and also alignment of the optical elements relative to the 

vehicle. 

49. Can alignment to vehicle be accomplished without major disassembly such as separating LM & MTV 

HUMAN FACTORS 

50. Discuss use of ATS controls back-up as well as primary ones. 

Can controls be operated in pressurized suit? 

51. Discuss means used to protect recon console optical components 

from damage that might be inflicted due to crew motions (e.g., 

ingress, egress, DPC loading ops, etc.) 

SPECS: 

52. What is status of your specs to subcontractors? is "A" Spec 

different than one included in Vol. I of the "A" PDR? 

53. Discuss any changes which are currently under negotiation. 

54. What are your recommended changes to Spec. data of ECP 17, 

particularly regarding elimination of the TBD's (TBR's etc.)? 

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55. GE delete the weight allocation from Subcontractor A for cue 

insertion. 

56. GE to provide drawing to AF/AS which identifies the location of 

the electrical penetration for the GE/sub A/DAC interface. 

57. GE to present its position on Subcontractor A weight and power 

at PDR. 

58. GE shall delete the requirement for the cue insertion function 

in Drive K. Space for the cue insertion function will be retained in Drive K. 

CONTROLS 

59. GE to present the results of its roll unbalance study at PDR. 

60. GE to perform a study to define the maximum allowable Alpha 

Subsystem pointing error consistent with the operational requirements resulting from the normal target acquisitions, 

boresighting, and slaved-mode functions. Further, GE will 

determine the detail alignment error allocations (GE/sub A/DAC) 

required to satisfy the maximum allowable Alpha pointing error 

defined earlier in the study. Based on the results of the 

study, GE will submit an ECP to modify the AVE-CEI Specification. 

61. GE to prepare an ECP to the AVE-CEI Specification clarifying 

the jitter pitch performance requirenent. (Tracking rate of 

.01 in pitch). 

62. GE to prepare an ECP to the AVE-CEI Specification relaxing the 

decoupling requirement from F 2° to F 5°. 

VISUAL DISPLAY PROJECTOR 

63. GE to prepare an analysis which will show the amount of focus 

adjustment required after insertion of a new film module. 

64. GE to examine the desirability of placing indexing marks on the 

focus adjustment knob to permit pre-pass focus adjustments. 

65. GE to conduct a trade study of impact of using Be in film 

module instead of Al. 

66. GE to define method for handling film modules during pre-pass 

briefings and target passes. 

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REPORT OF OPTICAL SIDE MEETING - ALPHA SUBSYSTEM - 3/7/68 

A meeting was held between D. Nicholson of Aerospace and 

A. C. Eckert and J. Denshaw of General Electric. The meeting 

centered on the degree of confidence that could be placed upon 

results obtained using computer programs in light of the 

limitations imposed by the mathematical techniques employed. 

It was agreed that the degree of confidence would be increased 

by further exchange of information. 

Prior to this side meeting, during the regular PDR 

meeting, it was agreed that GE would deliver the results of 

ITEK's off-axis analysis as soon as this analysis is received 

from ITEK. GE also expressed a strong desire to receive the 

results of Aerospace's computer analysis (CDC 6600), based 

upon ITEK's prescription, as soon as it is available. 

No action items resulted from the side meeting. 

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REPORT OF THERMAL SIDE MEETING 

Attendees: 

Harry Apoian 

G. Karp 

I. LJOR OPEN TIME LINE - Design Limits (Uses Target Profile) 

a. Gyro shell 0° to 100°F Allowable Range Gyro fluid 

controlled to 160° +5°F. 

b. Scanning mirror temp. gradient is limit on optical 

performance. Folding mirror not so critical. Need 

definition of optical perf. degradation vs temperature 

gradient. 

c. Temperature control with door position (penumbra cooling) 

will give only marginal benefits. Temperature control 

surface very closely follows sink temperature. 

1. Low °%05 coating (.2/.9) 

2. Low mass 

3. Sun "Blip" limits D/0 time to less than 45 mins. 

4. Instrumentation & controls required to position 

door for cooling. 

II. GYRO RELIABILITY - Not Known (Gene Ryan) (See Reliability t 

Presentation) 

Gyro heat pulse on backside of scanner will tend to 

reduce its temp. gradient, due to almost equal heat flux 

on both sides. 

ITEK contractual spec is: 

1. 25 mins/orbit, max. 

2. 50/720 hrs (7% duty cycle 100 mins/D max) 

3. Off-time max, 12 hrs (encoder may go to -20°F) 

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III. SHROUD POWER - 2.85 W +.15 Wheel 

12.5 +1.3W, 26 V Fine heater 

50 +5W, 26 V Coarse Heater, Warm-up 

Torquers 

Encoders 

IV. HI-THRUSTOR, 1500 Sec operation for orbit adjust. 

1. Peak shroud and insulation temps. reach equilibrium in 

less than 5 mins. 

800°F Shroud Max at 

175°F Insulation Stag pt. 

2. Thermal control coatings will withstand mix temps 

(being thermatrol investigated) 

3. 600 sec firing temp gradient is less severe than 

on-orbit operation (8 consecutive orbits). Will 

investigate 1500 sec firing. 

4. Degradation of coating due to contamination of ACTS 

firing not known. A comprehensive test and more 

suitable test time is necessary to resolve uncertainties. 

V. OPTICAL PERF. DEGRADATION AS A FUNCTION OF TEMP. GRADIENT 

1. ITEK currently evaluating optical system performance as 

effected by thermal and mechanical perturbances 

(due 1 May). Performance degradation caused by hot 

case under study, 25 mins door open. Effect on perf. 

due to temp. gradient only (D/0) not known and unknown 

if capability exists. (Elg. method unknown to ITEK) 

VI. FAILURE MODE - OPEN DOOR CONDITIONS FAILURE ANALYSIS 

ITEK currently studying effect of D/0 failure, on optical 

system performance degradation. Due approx. 1 May. 

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SUBJECT: SIDE MEETING WITH AEROSPACE AT ALPHA PDR 

ATTENDEES: M. PAVLICK - GE 

J. BENNETT - Aerospace 

W. CROOKER - Aerospace 

PURPOSE OF MEETING 

Review Itek drawings and discuss design evolution design criteria and 

discuss the effects of shell pressure distortions on the telescope and shear web. 

DISCUSSION AND RESULTS 

The Itek drawings of the telescope, scanner and fixed-fold mirror and the 

shroud were reviewed in detail. The design concepts were discussed along with 

their evolution. The design concepts behind the telescope restraints were discussed. 

It was shown by GE that, if the shear tie was not used in the present configuration, 

serious deflection and structural frequency problems would exists. It was also shown 

using very preliminary calculations, that when the shell is pressurized, the stresses 

induced into the telescope tube and the shear web would be minimal. It was also 

shown that the angular rotation of the telescope with respect to the penetration 

fitting would be approximately 1.34 arc sec. Copies of these calculations were transmitted to J. Bennett for his information. A discussion was also held on the shroud 

design and its evolution. 

/ av--44:e 

M. J. PAVLICK - GENERAL ELECTRIC 

BENNETT - AEROSPACE 

W. CROOKER - AEROSPACE 

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ACQUISITION SUBSYSTEM REQUIREMENTS 

THIS PRESENTATION WILL, 

(1) SUMMARIZE OBJECTIVES OF THE ACQUISITION SUBSYSTEM 

(2) SUMMARIZE MAJOR REQUIREMENTS (SPDR & CEI) 

(3) DISCUSS STATUS OF GE COMPLIANCE WITH THOSE 

REQUIREMENTS WHERE PARTICULAR PROBLEMS OR 

RISK EXIST 

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ACQUISITION SUBSYSTEM OBJECTIVES 

INCREASE DORIAN SYSTEM EFFECTIVENESS BY MARRIAGE OF 

MAN AND SENSORS TO PERFORM THE FOLLOWING: 

1. SELECTION OF OPTIMUM TARGETS FOR PHOTOGRAPHY BY, 

- WEATHER EVALUATION 

- TARGET ACTIVITY EVALUATION 

2. OPTIMIZE PHOTOGRAPHIC RESOLUTION BY CENTERING 

TARGETS IN THE FORMAT VIA "POSITION UPDATE". 

3. PERFORM RATE NULLING AND TARGET CENTERING FOR 

THE MAIN OPTICS IN THE EVENT OF IVS OR VISUAL 

OPTICS FAILURE. 

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ABI LI TYTO VARY OBSERVED SCENE BRI GHTIMSS 

0 0 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 "MIL SPECIAL HANDLING 

S.P.D.R. REQUIREMENTS 

1) PROVIDE TWO ACQUISITION TELESCOPES WITH, 

3.6 FEET/L.P. RESOLUTION 

127 X +5X MAGNIFICATION MAX. 

16 X +1X MAGNIFICATION MIN. 

2: 1 ZOOM CAPABILITY - HIGH AND LOW RANGE 

4° MINIMUM F.O.V. 

2) EACH CREW STATION WILL DISPLAY 1 ATS AND BE CAPABLE OF 

DISPLAYING THE VISUAL OPTICS IMAGE 

3) MANUAL CONTROLLER INPUTS SHALL BE ACCEPTED FOR THE ATS 

AND M.O. FROM EACH CREW STATION 

4) IT SHALL BE POSSIBLE TO SLAVE THE M.O. TO THE ATS L.O.S. 

5) IT SHALL BE POSSIBLE TO AUTOMATICALLY CALL UP AND DISPLAY 

CUEING AIDS TO THE CREW 

24 

—Steftif SPECIAL HANDLING 
CD V 

• • • cat: 

C.) 

CD CA 

•0 0 

NRO APPROVED FOR 

RELEASE1 JULY 2015 

I 

'MKT_ SPECIAL HANDLING 

• 25 

SPECTALKIWZLING 

•■■ 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 ife-R-EL SPECIAL HANDLING 

ATS OPTICAL REQUIREMENTS 

RESOLUTION: 3.3 FEET "STATIC" AT 80 NM AND 2: 1 

CONTRAST RATIO (HIGH POWER) 

MAGNIFICATION: 16 +1X TO 32 X,63.5 X TO 127 X +5, - 3 X 

FIELD OF VIEW: 4 DEGREES AT 16 X 

1 DEGREE AT 63.5 X 

SCAN FIELD: +70° TO -40° IN PITCH 

+45° TO -45° IN ROLL 

VIGNETTING: NONE FROM +10° TO +40° PITCH 

+35° TO -35° ROLL 

LESS THAN 60% EVERYWHERE IN THE SCAN 

FIELD 

PERIPHERAL DISPLAY: 

RETICLE: 

EYE RELIEF: 

FILTERS: 

TIME COUNTDOWN AND REFERENCE, 

TARGET INFORMATION, ETC. 

CIRCLE INDICATING HIGH ZOOM F.O.V. - 

CROSS HAIRS 

0.40" MIN, (0.7") 

FOUR - UNDEFINED 

26 

S'ECIAL 1ANDLINC/ 
NRO APPROVED FOR 

, RELEASE 1 JULY 2015 SPECIAL HANDLING 

e 

• 

• 

, '• 

27 

Q-7 —,:lEDRIL SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 '"Ileft-E-T-- SPECIAL HANDLING 

ATS CONTROLS REQUIREMENTS 

1. POINTING ACCURACY (AUTO) 8 MINUTES AFTER BORESIGHTING 

2. POINTING ACCURACY (CREW/MCS) 2 MINUTES 

3. TRACKING RATE ACCURACY 540 RAD/SEC. 

4. L.O.S. FILTER 1/4 ARC SECOND 2Cr 

5. IMAGE ORIENTATION +5° AT END OF SLEW 

6. RECOUPLING +2° 

7. SLAVE RATE ACCURACY 100A RAD/SEC. 

8. BLANKING PREVENT SOLAR VIEWING 

9 BORES IGHTING PROVIDE ON ORBIT ALIGNMENT CORRECTIONS 

10. ZOOM RESPONSE 0.5 SECONDS END TO END 

28 

l'EGREL SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 '---Stelit-EL SPECIAL HANDLING 

RESOLUTION & JITTER 

MISSION GOAL 

3.6 FEET LINE PAIR 

RESOLUTION ON-ORBIT 

AT 80 N.M. 

V 

S.P.D.R. 

3.6 FEET/LINE PAIR 

RESOLUTION ON-ORBIT 

AT 80 N.M., AND 2:1 

CONTRAST RATIO 

CEI SPEC 

REQUIREMENT REQUIREMENT 

ARC RECORD 

MAX. L.O.S. JITTER 

GOAL 

3.3 FEET "STATIC" 3.6 FEET DES. 

RESOLUTION ON-ORBIT ON-ORBIT 

ir 

 _ . 

DESIGN 

ATS COMPONENT SPEC SERVO & STRUCTURE REQ, 

REQUIREMENT REQUIREMENT 

ARC SECONDS MAX. L.O.S. 

JITTER 

3.0 FEET 

RESOLUTION 

IN AN ISOTHERMAL 

ENVIRONMENT 

3.3 FEET RESOLUTION 

IN AN ON-ORBIT 

ENVIRONMENT 

OPTICAL, THERMAL'', 

L&STRUCTURE DES." 

k 

OPTICAL DES.': BEARING ENCODERS 

• . DESIGN; DESIGN / 

29 STRUCTURE DESIGN) 

ECIAL HAN' it4C, 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

--Stefig SPECIAL HANDLING 

ATS RESOLUTION 

REQUIREMENT: THE STATIC HIGH POWER RESOLUTION OF THE ATS AT 80 NM ALTITUDE 

SHALL BE 3.3 FEET/LINE PAIR OR LESS, ON AXIS, WHEN THE 

CONTRAST RATIO IS 2.1. 

PROPOSED CEI CHANGES: EXCLUDE EFFECTS OF CONTAMINATION FROM SOURCES 

OTHER THAN GE EQUIPMENT. 

RESULTS OF ANALYSIS TO RATE: 

1) ALL GE ANALYSIS, WHICH TREATED LESS THAN WORST CASE ERROR 

BUILDUPS, YIELDED RESOLUTION OF 3.3 FEET OR LESS. 

2) ALL ITEK ANALYSIS SUBMITTED TO DATE INDICATES THAT 3.3 FEET 

RESOLUTION IS ACHIEVABLE, BUT THAT A TIGHT TOLERENCE BUDGET 

IS NECESSARY. 

3) GE ANALYSIS WITH A WORST CASE TOLERENCE BUILDUP YIELDED A 

RESOLUTION OF 3.4 FEET. 

COMMENTS: 

1) ANALYSIS IS BASED ON THE "SCHADE" VISUAL THRESHOLD CURVE. 

THIS CURVE HAS NOT BEEN VERIFIED EXPERIMENTALLY. THE USE OF 

THE "LOWRY-DE PALMA" CURVE WOULD YIELD BETTER RESULTS. 

2) ANALYTICAL RESULTS ARE APPROXIMATE! THE RESULTS ARE A 

FUNCTION OF THE NUMBER OF RAYS TRACED, NUMBER OF COLORS 

CONSIDERED, AND OTHER FACTORS RELATING TO THE ANALYTICAL 

TECHNIQUES EMPLOYED. 

3) ANALYSIS DOES NOT PROVIDE FOR RESOLUTION DEGRADATION DUE TO 

CONTAMINATION OF THE OPTICAL SURFACES. INHIBITS FOR WASTE 

MANAGEMENT, MOLECULAR SIEVE, AND FUEL CELL WATER ARE NOT 

3" 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 '--Ifeff-T- SPECIAL HANDLING 

PRESENTLY PROVIDED, 

4) THERMALLY INDUCED RESOLUTION DEGRADATION IS DIFFICULT 

TO ANALYZE. THE MAINTAINANCE THERMAL EFkJCTS OR THE 

EXTERNAL MIRRORS ARE EXPECTED TO BE PARTICULARLY 

CRITICAL. 

5) THE FOLLOWING DUTY CYCLY IS ASSUMED IN THE DESIGN 

a) MAX. OPEN TIME PER ORBIT IS 25 MINUTES 

b) MAX. OPEN TIME PER DAY IS 120 MINUTES 

c) SHROUD DOOR OPEN 50 HOURS PER MISSION 

31 

SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 Iff-11-ET. SPECIAL HANDLING 

OFF AXIS RESOLUTION 

REQUIREMENTS: 

A. WITHIN 10 DEGREES OF THE CENTER OF THE APPARENT F.O.V. THE RESOLUTION 

SHALL BE TBD 

B. AT THE EDGE OF THE F.O.V. THE RESOLUTION SHALL BE TBD. 

POSSIBLE CEI CHANGES: 

INCLUDE THIS INFORMATION IN SECTION 6. 

PROBLEM: 

ANALYTIC PREDICTION OF OFF-AXIS PERFORMANCE IS DIFFICULT DUE TO ASTIGMATIC 

EFFECTS. 

POSSIBLE SOLUTIONS: 

A. PUT PREDICTED PERFORMANCE IN SECTION 6 AS INFORMATION. 

B. USE SUBCONTRACTOR DATA TO FILL IN THE TBDI S IN SECTION 3, WITH SUFFICIENT 

MARGINS. 

32 

""ligAil. SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

---SMET—SPECIAL HANDLING 

TIME REQUIRED TO ACHIEVE 3.3 FEET RESOLUTION ON-ORBIT 

REQUIREMENT: A. NO REQUIREMENT EXISTS CONCERNING THE TIME ON ORBIT WHEN THE 

SYSTEM MUST BE OPERATING IN SPEC. 

B. D.A.C. LIMITS SEAL LEAKAGE TO 100 ac/LINEAR INCH FOR BOTH 

WINDOW AND OBJECTIVE LENS. 

PROBLEM: 

THE SPACE BETWEEN THE ATS OBJECTIVE LFITS AND THE TELESCOPE MUST BE VENTED TO 

ANALYZE PRESSURE ACROSS THE LENS BEFORE FULL RESOLUTION CAN BE ACHIEVED. 

POSSIBLE SOLUTIONS: A. OBTAIN CUSTOMER OR D.A.C. O.K. TO PROVIDE CONTINUOUS 

600 cc/LINEAR INCH LEAK. 

B. PROVIDE VALVE WHICH WOULD BE CLOSED IN THE EVENT OF WINDOW 

FAILURE. 

33 

-SteRELSPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

--Miff- SPECIAL HANDLING 

DYNAMIC RESOLUTION 

CEI DESIGN GOAL - THE ATS WILL RESOLVE 3.6 FEET BAR PAIRS FROM 80 N.M. ALTITUDE 

WHEN THE CONTRAST RATIO IS 2:1. 

COMMENTS: 

1. INDEPENDENT GE AND ITEK ANALYSIS HAS SHOWN THAT THE GOAL WILL BE MET WHEN 

MONOTONIC L.O.S JITTER DOES NOT EXCEED 4 ARC RECORD HALF-AMPLITUDE. 

2. A "JITTER TEST" IS BEING SET UP AT ITEK TO EXPERIMENTALLY VERIFY THE ANALYTIC 

PREDICTIONS OF RESOLUTION IN THE PRESENCE OF MONOTONIC JITTER, AND TO DETERMINE 

THE VISUAL THRESHOLD. 

3. ACTUAL SYSTEM L.O.S. JITTER WILL BE RANDOM, NOT MONOTONIC! 

EFFECT OF RANDOM JITTER NOT DETERMINED BY ANALYSIS OR EXPERTMANT 

34 

SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 ifeRET-SPECIAL HANDLING 

L.O.S JITTER 

REQUIREMENT: IN AUTOMATIC OPERATION, COMBINED DRIFT AND JITTER ERROR SHALL BE 

LESS THAN SHOWN IN FIG. 1, EXCLUSIVE OF; 

A) EFFECTS OF OV RATES DUE TO NON-GE EQUIPMENT 

B) EFFECTS OF ATS GIMBAL RATES BELOW 0.01 DEG./SEC. 

PROPOSED CEI CHANGE: NONE AT PRESENT 

/1 A 

7"1 ,7 

G,03z. GAS 

C fLY 

/ ,• 

35 

—MKT-SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

--Staff-SPECIAL HANDLING 

JITTER PERFORMANCE (CONT) 

PROBLEM: AVAILABLE ENCODER NOISE DATA INDICATES THAT A 19 OR 20 BIT ENCODER IS REQUIRED 

WITH PRESENT "RATE PLUS POSITION DESIGN". PRESENT DESIGN INCLUDES 18 BIT ENCODER. SPACE NOT AVAILABLE FOR 20 BIT ENCODER. 

POSSIBLE SOLUTIONS 

A) DESIGN PITCH LOOP AS A PURE RATE LOOP. 

B) PROVIDE 19 OR 20 BIT ENCODER 

C) CHANGE CEI SPEC TO APPLY THE JITTER REQUIREMENT ONLY TO A LIMITED PORTION 

OF THE SCAN FIELD 

PROBLEM: THE "POSITION PLUS RATE" PITCH LOOP WILL NOT PERMIT TRACKING WITHIN SPEC TO 

0.01°/SEC EVEN WITH THE 20 BIT ENCODER. 

POSSIBLE SOLUTION: 

A) CHANGE CEI SPEC. 

B) CHANGE DESIGN TO A PURE RATE LOOP. 

36 

"--IfeRET-- SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SECRET SPECIAL HANDLING 

JITTER REQUIREMENT (CONT) 

PROBLEM: A DYNAMIC MODEL IS NOT YET AVAILABLE TO PERMIT THE CONTRIBUTION 

OF THE STRUCTURE TO JITTER TO BE EVALUATED. 

SOLUTION: A DYNAMIC MODEL IS BEING DEVELOPED TO PERMIT EVALUATION OF 

STRUCTURALLY INDUCED L.O.S. JITTER. 

37 

SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 --IfekET—SPECIAL HANDLING 

VIGNETTING 

REQUIREMENT: THERE SHALL BE NO VIGNETTING BETWEEN +100 AND +40° IN PITCH AND 

BETWEEN + 35 IN ROLL (REF. TO VEHICLE CO-ORDINATES). VIGNETTING 

SHALL NOT EXCEED 60% ANYWHERE IN THE SCAN FIELD. 

PROPOSED CEI CHANGE: T.B.D. 

PROBLEM: PRESENT DESIGN YIELDS AS HIGH AS 80% VIGNIalING (AT 70° FORWARD 

AND 45° OUTBOARD). VIGNETTING DOES NOT EXCEED 60% AT PITCH ANGLES 

BELOW +60 DEGREES. 

PROPOSED SOLUTION: REVISE CEI SPECIFICATION 

38 

--IR-RR- SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 -SEC-14T- SPECIAL HANDLING 

POINTING ACCURACY 

REQUIREMENTS: AFTER ON-ORBIT BORESIGHTING THE ATS SHALL BE POINTED TO 

THE TARGET TO WITHIN + 8 ARC MINUTES, TWO SIGMA, NEGLECTING ERRORS DUE 

TO EPHEMERIS AND TARGET LOCATION INFORMATION, AND ASSUMING O.V. STRUCTURAL 

DEFORMATION DOES NOT CONTRIBUTE MORE THAN 0.5 MIN. L.O.S. ERROR. 

PROPOSED CEI CHANGES: 

I. EXCLUDE EFFECTS OF VISUAL OPTICS MISALIGNMENTS WHICH 

EXCEED TBD MINUTES OF ARC. 

2. CHANGE PERMISSABLE POINTING ERROR FROM 8 TO 10 MINUTES. 

STATUS: THE E.A.R. CONTAINS AN ERROR ANALYSIS WHICH DEMONSTRATES COMPLIANCE 

WITH THIS REQUIREMENT IF: 

a) DEFLECTIONS OF THE D.A.C. STRUCTURE AFIhR BORESIGHTING DO 

NOT CAUSE MORE THAN 0.5 ARC MINUTES OF L.O.S. POINTING 

ERROR AS STATED IN THE GE, CEI SPEC. 

b) THE RELATIVE ALIGNMENT ERRORS, ON-ORBIT BEFORE BORESIGHTING, BETWEEN THE SEVERAL ATS COMPONENTS, AND BETWEEN 

CERTAIN MAIN OPTICS COMPONENTS, DO NOT EXCEED THE VALUES 

ASSUMED IN THE ANALYSIS. 

PROBLEMS: 

1) POST BORESIGHTING POINTING ACCURACY IS A FUNCTION PREBORESIGHTING ERRORS DUE TO GROUND ALIGNMENT TOLERANCES, 

L.M. PRESSURIZATION, "L-G" RELIEF, ETC. LM PRESSURIZATION 

IS EXPECTED TO INTRODUCE SIGNIFICANT ERROR. 

39 

--Sfe-Ri-T- SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

2) D.A.C. HAS NOT AND IS NOT EXPECTED TO ACCEPT INTERFACE 

SPEC. LIMITATIONS FOR ON-ORBIT ALIGNMENT ERRORS WHICH 

ARE CONSISTANT WITH THOSE ASSUMED IN THE ANALYSIS. 

3) IT IS BELIEVED THAT THE D.A.C. STRUCTURE MAY CAUSE MORE 

THAN 0.5 ARC MINUTES OF L.O.S. ERROR DUE TO DEFLECTIONS 

AFTER BORESIGHTING. (GE IS PROTECTED IN THE CEI AGAINST 

THIS EVENTUALITY.) 

4) GE DOES NOT HAVE AN INTERFACE SPEC. GUARANTEE OF THE 

ALIGNMENT OF THE VISUAL OPTICS. 

POSSIBLE SOLUTION: 

A. INCREASE THE COMPLEXITY OF THE BORESIGHT ROUTINE TO 

PERMIT REMOVAL OF ALIGNMENT ERRORS BETWEEN THE IbLDING 

MIRROR AND THE SCANNER. 

B. USE D.A.C. ANALYTICAL PREDICTIONS OF STRUCTURAL DEFECTIONS 

TO DETERMINE ON-ORBIT COMPONENT ALIGNMENT. 

C. MOUNT THE SCANNER AND THE HOLDING MIRROR TO A CONNECTING 

STRUCTURAL ELEMENT RATHER THAN DIRECTLY TO THE PRESSURE 

SHELL. 

STATUS: 

A. EXPANDED BORESIGHT ROUTINE EQUATIONS WRITTEN AND EVALUATED. 

MATHEMATICAL FEASABILITY HAS BEEN DEMONSTRATED. COMPATABILITY 

WITH SOFTWARE CAPACITY IS BEING EVALUATED. 

B. D.A.C. HAS BEEN REQUESTED TO RE-EVALUATE THE POSSIBILITY OF 

ALIGNING THE ATS HARDWARE ON A PRESSURIZED L.M. 

40 

"Ife-RET--- SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

TRACKING RATE 

REQUIREMENT: AT THE END OF SLEW THE L.O.S. RATE ERROR SHALL BE LESS 

THAN 540.1+. RAD/SEC. 

POSSIBLE PROBLEM AREA: POSITION ERRORS BEFORE BORESIGHTING WILL 

INTRODUCE RATE ERRORS WHICH ARE NOT PRESENTLY 

CONTAINED IN THE ERROR ANALYSIS RELATIVE TO 540 

.61- RAD/SEC. 

41 

----SEMEL SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SECRET SPECIAL HANDLING 

SOLAR BLANKING 

REQUIREMENT: AUTOMATIC BLANKING PROVISION SHALL BE INCORPORATED TO 

PREVENT CREW INJURY RESULTING FROM INADVERTANT SUN 

VIEWING THROUGH THE ATS. 

PROPOSED CEI CHANGE: "THE CONTRACTOR SHALL NOT BE RESPONSIBLE FOR EYE 

DAMAGE RESULTING FROM CAUSES OTHER THAN DIRECT 

VIEWING OF THE SUN." 

42 

nr #.* f IL r ■. I 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

THERMAL 

PROPOSED NEW CEI PROVISION: INCORPORATE D.A.C. SUPPLIED THRUSTER 

PLUME CHARACTERISTICS WITH CEI SPEC. VS 

DESIGN BASELINE. 

REASON: SHROUD THERMAL DESIGN DEPENDANT ON THIS INFORMATION. 

POSSIBLE PROBLEM AREA: THE EFFECTS OF CONTAMINATION FROM WASTE 

MANAGEMENT, THRUSILKS, ETC., ON THERMAL 

COATINGS HAS NOT BEEN DETERMINED. 

43 

SECRET SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

MANUAL CONTROL STICK CONTROL 

OF THE MAIN OPTICS 

QUESTION: IS THE FIRST STICK TO GO INTO THE VISUAL OPTICS RANGE THE CONTROLLING STICK? 

IS THE RIGHT HAND STICK STILL CONTROLLED BY THE MAGNIFICATION STICK WHEN IN 

THE MAIN OPTICS RANGE? 

I. THE DECISION AS TO WHICH, IF EITHER OF THE TWO MC'S CAN CONTROL THE MAIN OPTICS IS A 

FUNCTION OF; 

A) THE STATUS OF THE LEFT-RIGHT-AUTO SWITCH. 

B) THE STATUS OF THE IVS, MANUAL-IVS SWITCH. 

C) THE RANGE OF EACH MAGNIFICATION CONTROL STICK. 

D) WHICH OF THE TWO ATS'S WAS ASSIGNED THE TARGET FOR OBSERVATION? 

2. WHEN OPERATING IN THE AUTO MODE, ONLY THE CREW STATION WHICH WAS ASSIGNED THE TARGET FOR 

OBSERVATION CAN CONTROL THE MAIN OPTICS WITH THE MCS, AND THEN ONLY WHEN 

A) THE IVS IS IN THE MANUAL POSITION 

B) THE MAGNIFICATION STICK IS IN THE MAIN OPTICS RANGE. 

3. WHEN THE SWITCH IS IN THE LEFT (OR RIGHT) POSITION THE CREW MEMBER AT THE LEFT (OR RIGHT) 

CONSOLE CAN GET CONTROL OF THE M.O. IF: 

A) THE IVS IS OFF 

B) THE MAGNIFICATION STICK IS IN THE M.O. RANGE 

44 -1' T- SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 "IfOR-E4 SPECIAL HANDLING 

VISUAL OPTICS AVAILABILITY AT A CREW STATION 

THE VISUAL OPTICS WILL BE AVAILABLE AT A CREW STATION WHENEVER 

A) THE LEFT - RIGHT -AUTO SWITCH IS IN THE AUTO POSITION AND THE M.O. 

TARGET WAS ASSIGNED TO THAT CREW STATION OR, 

B) THE LEFT - RIGHT - AUTO SWITCH IS IN POSITION REPRESENTATIVE OF THAT 

CREW STATION. 

45 

Ife SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 'MEL SPECIAL HANDLING 

CUE SYSTEM OBJECTIVES AND OPERATIONAL FEATURES 

GENERAL: AID CREW IN LOCATING TARGETS AND RECOGNIZING ACTIVITY 

PRE - PASS: 

- PROVIDE HIGH RESOLUTION SCENES FOR STUDY 

- CUES CALLED UP BY COMPUTER COMMANDS, IN ORDER, 

WHEN REQUESTED VIA THE KEYBOARD 

- STUDY TIME IS REGULATED BY CREW 

- ALPHA-NUMERIC DISPLAYED WITH EACH CUE 

ON-TARGET 

- PROVIDE MEDIUM RESOLUTION CUES WITH SUFFICIENT 

F.O.V. TO INCLUDE "LANDMARK" AIDS FOR TARGET 

LOCATION 

- CUES CALLED UP AUTOMATICALLY WITHOUT CREW COMMANDS 

- CUE DWELL TIME CONTROLLED BY COMPUTER ( 2 SEC.) 

CREW CAN OVERRIDE 

- ALPHA-NUMERIC DISPLAYED WITH EACH CUE 

- TWO MODULE INTERCHANGES CAN BE MADE DURING PASS, 

EACH WITHIN 10 SECONDS 

46 

---S-EG441, SPECIAL HANDL ING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 -1-MEL. SPECIAL HANDLING 

CUE PROJECTOR REQUIREMENTS 

RESOLUTION: 228 LINE PAIRS/MM ON FILM FOR 

6: 1 CONTRAST RATIO 

SCREEN SIZE: 6.5 INCHES 

SCREEN BRIGHTNESS: 0 - 15 FOOT LAMBERTS 

CUE RETRIEVAL: 0.45 SECONDS + /100 SEC. 

MANUAL FRAME SELECT: - OCTAL FORMAT 

MODULE STORAGE: 16 MODULES (8 EACH) 

ALPHA NUMERIC RETRIEVAL: - 0.3 SEC. 

47 

"IfeRET-- SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 --1-EREL SPECIAL HANDLING 

MSS/oN OD Ile /we AID IN IDENTIFYING AND 

LOCATING TARGETS AND 

ACTIVITY INDICATORS 

SPD2 CUE SYSTEM 

OPEN LOOP COMMANDS TO CUE SYSTEM 

FOR AUTO. PRESENTATION OF CUES. 

iCUE SYSTEM 

PROVIDE FOR:(@ EACH RECON CONSOLE) 

AO DISPLAY 

CUE D/SPLAY 

CONTROLS 

PROVIDE 6 CHARACTER oc-N 

CUE PROJECTOR SHALL: 

DISPLAY OS" FILM ON 6.5"D/11 SCREEN 

MTF @ I LP/MM 2-• 043 

CUES 

DISPLAY WITHIN [0.4.5.+4] SEC AFTER 

RELEASE OF PREVIOUS CUE. 

VDP SATISFY REQM'TS WITH 6:1 CONTRAST 

RAT/0 /DENT. CODE ON GFE FILM 

11■111111M DISPLAY CUE FOR K2 SECS. 

RELEASE CUES WHEN TGT BUTTON AS ACTUATED 

HOLD CUES WHILE "HOLD...BUTTON IS DEPRESSED 

PROVIDE CONTROL FOR Dks'PLAY AUTO. DURING ReERASS 

PROVIDE CONTROL -FOR CUE GALLUP 1,1y0 COMPUTER 

PROCESSING 

...]

FILM MODULES 

STORAGE FOR /6 FILM MODULES. 

VDP PRESENT UP TO 4094 SEPERATE 

CUE FRAMES/MODULE 

FILM MODULE EXCH 5 /0 SECS DURING TGT PASS 

RESOLUTION 

CUEE RESOLUTION W/6:I CONT RATIO TARGET. 

NEAR CENTER OF SCREEN 228 LP/MM 

NEAR EDGE OF SCREEN 204.5- LP/MM 

CUE SCREEN BRIGHTNESS (VARIABLE) 

NEAR CENTER OF SCREEN 0 TO /5 FT LAMBERT. 

NEAR EDGE- OF SCREEN a //2 @ CENTER 

...1

o(-N 

DISPLAY WITHIN 0.3 SEC AFTER START OF SLEW 

.0/SPLAY AT SAME TIME SCREEN CUES 

ARE PROJECTED 

RELEASE WHEN TGT BUTTON /..c ACTUATED 

48 

*--1-EGREL SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 1- SPECIAL HANDLING 

FILM MODULE INTERCHANGE DURING TARGET PASS 

REQUIREMENT: THE CREW STATION SHALL BE DESIGNED SUCH THAT A VDP FILM 

MODULE CAN BE INTERCHANGED DURING A TARGET PASS WITHIN 

10 SECONDS. 

COMMENT: PRESENT DESIGN WILL PERMIT TWO MODULES TO BE STORED AT 

EACH CREW STATION TO PERMIT THIS REQUIREMENT TO BE NET. 

WILL MORE THAN TWO MODULE CHANGES BE REQUIRED DURING A 

PASS? 

49 

'Hag- SPECIAL HANDUNG 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

-MIK+ SPECIAL HANDLING 

VDP USER FILM 

PROPOSED NEW CEI PROVISION: TEST FILM FOR MEASURING VDP RESOLUTION 

SHALL BE SUPPLIED BY THE GOVERNMENT. 

REASON: 

1. TO PREVENT THE SUBCONTRACTOR FROM DUPLICATING FILM 

DEVELOPMENT PROGRAMS UNDERTAKEN BY THE AIRFORCE. 

HAS NOT FOUND A VENDOR TO SUPPLY 228 LINE PAIR/MM ON 

1304 FILM. 

2. TO INSURE COMMONALITY BETWEEN THE USER AND TEST FILMS. 

50 

SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

---SfeRET-- SPECIAL HANDLING 

INTERFACE STATUS 

AC601SITION OPTICS/LAB MOOULE 

1. 00CUMENTAT I ON 

2. AGREEENTS ON IATERFACE EWUIRE'iviEATS 

3. INTERFACES COVE .J I ■1 I FS MOL-707003 

I Cid-O25 

4. INTERFACE PROBLEivl NOT JOCUMENTE0 

51 

7IfOWL PF "AL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 '1"EGREL SPECIAL HANDLING 

1. DOCUMENTATION 

ICN-025 TO IFS-MOL-707003, LAB MODULE 

TO GE-AVE 

ICU-MOL-707001, SHEET 11, MECHANI3AL 

INTERFACE DRAWING 

ICO-MUL-707022, EuUIPMENT SPACE 

ALLOCATION 

- ICD-MUL-707031, ACCESS SPACE ALLOCATION. 

52 

*-SICALL. SPECIAL HANDLING 
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SUBSYSTEM DESCRIPTION 

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ALPHA .SUBSYSTEM PEAK AND AVERAGE POWER SUMMARY (WATTS) 

78 

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SHROUD 

N 

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m g 

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36. 0.1 1.3 

9.5 0.02 

3.5 0.01 

16. 0.04 

2.5 2.5 2.5 

20. 20. 

9.4 9.4 0.62 

0.5 0.5 

0.5 0.5 

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61.5 3.12 

8.5 0.83 

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2.5 2.5 2.5 

69.5 

4.0 

12. 

4.0 

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36.9 36.9 

3.4 3.4 

1.7 1.7 

17.3 5.4 6.69 

2.19 

2.19 

2.1 

1.0 

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7.2 7.2 

1 44. 44. (8.42 

155.61 199.53 181.01 21.6 

27.37 

311.21 399.06 362.02 43.2 

420. 

54.74 

50. 

Torque Motor IA 

Torque Motor OA 

Prism Actuator 

Zoom Actuator 

Power Changer Actuator 

Sun Shield Motor 

Shroud Actuators 

Encoders (2) 

Prism Feedback 

Zoom Feedback 

Power Changer Feedback 

Sun Shield Feedback 

Peripheral Display 

Sun Sensor 

Gyro Warmup Heater IA 

Gyro Control Heater IA 

Gyro Electronics IA 

Gyro Spin Motor IA 

Gyro Torquer IA 

Gyro Electronics, Htr., Etc., OA 

Drive K Electronics K0,K3 thru K10 

DKE K2 Modules, IA and OA 

DKE Torquer Power Amplifier, IA 

DKE Torquer Power Amplifier, OA 

DKE Power Amplifier, Pr'ism 

DKE Power Amplifier, Zoom 

DKE Power Amplifier, Power Changer 

DKE Power Amplifier, Sun Shield 

DKE Power Amplifier, Shroud 

DKE Power Amplifier, IA and OA Gyro Torquers 

Visual Display Projector 

Total Peak, per Crew Station 

Total Average, per Crew Station 

Total Peak, per Subsystem 

Total Worst Case Peak Allocation 

Subsystem Average 

Allocated Average 

'Mg- SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

-Ifei-EL., SPECIAL HANDLING 

ACQUISITION SUBSYSTEM 

WEIGHT STATUS SUMMARY 

OCTOBER 1967 

STATUS (LBS.) 

CURRENT BEST 

ESTIMATE (LBS.) 

DELTA 

(LBS.) 

GE COMPONENTS 165 165 0 

DRIVE K ELECTRONICS 40 74 + 34 

SUBTOTAL 205 239 + 34 

ITEK 329 344 ± 15 

.... 

TOTAL 534 583 + 49 

EST. CALC. ACT. EST. CALC. ACT. 

PERCENTAGE BREAKDOWN 100 66 31 3 

79 

-11E-13441-1._ DUNG 
UISITION SUBSYSTEM WEIGHT 

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CRITICAL SUBSYSTEM ANALYSIS 

CONTROLS ANALYSIS 

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NRO APPROVED FOR 

RELEASE 1 JULY 2015 l'EGREL SPECIAL HANDLING 

TABLE 2.2-1. RATE SERVO CONFIGURATION ERROR SUMMARY 

(JITTER PERFORMANCE) 

ERROR SOURCE PITCH AXIS 

Bearing Noise 0.043 sec 

Gyro noise 

Loop Electronic Noise 

Input Noise (D/A) 

ROLL AXIS 

0.0143 sec 

0.023 ,,ee 

0.016 sec 

0.022 see 

0.023 sec 

0.016 sec 

0.022 61;e 1

RMS Gimbal Error 0.054 sec 0.0375 see 

RMS LOS 0.1105 sec 

0.221 sec 

89 

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LOW BEARING NOISE REJECTION 

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MAX ERROR RESULTING FROM VEHICLE TRANSIENTS 

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RELEASE 1 JULY 2015 - "-Si

feRiLSPECIAL HANDLING 

TABLE 2.2-2. POSITION SERVO CONFIGURATION ERROR SUMMARY 

ERROR SOURCE PITCH ROLL 

-1 

Bearing Noise 0.18 sec 0.165 sec 

Electronic Noise 0.016 sec 0.016 sec 

Quantizing Error 0.025 sec 0.062 sec 

RMS Gimbal = 0.182 sec 0.172 sec 

RMS LOS = 0.403 sec 

20' LOS = 0.806 sec 

92 

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DISADVANTAGES 

SED COMPLE

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MAXIMUM BEARING NOISE REJECTION 

POSITION + RATE CONFIGURA

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RELEASE 1 JULY 2015 "SIC-REL SPECIAL HANDLING 

POSITION + RATE PERFORMANCE 

PITCH ROLL 

Bearing Noise .02 .007 

Gyro Noise .022 .023 

Electronic Noise .016 .016 

Quantizing Noise .0125 .068 

RMS Gimbal .037 .074 

RMS LOS 0.105 Sec 

2 d LOS 0.21 

95 

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PERFORMANCE COMPARIS

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BASELINE PERFORMANCE 

TABLE 2.2-4. PRIMARY MODE ERROR SUMMARY 

PITCH ROLL 

Bearing Noise 0.02 sec 0.026 sec 

Electronic Noise 0.016 sec 0.022 sec 

Gyro Noise 0.022 sec 0.023 sec 

Input Noise 0.016 sec 

Quantizing Noise 0.0125 sec 

RMS Gimbal error - 0.037 sec 0.0434 sec 

■■• 

&PIS LOS - 0.086 sec 

2 LOS - 0.172 sec 

BACKUP MODE ERROR SUMMARY 

PITCH ROLL 

, Bearing Noise 0.180 sec 0.165 sec 

Electronic Noise 0.016 sec 0.016 sec 

Quantizing Noise 0.0125 sec 0.062 sec 

RMS Gimbal - 0.182 sec 0.172 sec 

RHS LOS - 0.403 sec 

2 LOS - 0.806 sec 

98 4. I 0.1 f\ Itf, v
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CONSTRAINTS 

STRUCTURE 

COMMAND RATE (100cps) 

INCORPORATION IN SLEW SERVO 

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99 

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ERROR ANALYSIS 

BASELINE NEW DATA 

J = .12 ROLL J = .08 ROLL 

J = .36 PITCH J = .25 PITCH 

20 BIT ENCODER 19 BIT ENCODER 

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BEARING NOISE 0.02 0.026 .009 .01 

GYRO NOISE 0.022 0.023 .022 .023 

ELECTRONIC NOISE 0.016 0.016 .016 .016 

QUANTIZING ERROR 0.0125 .12 

INPUT NOISE 0.022 .022 

RMS GIMBAL 0.037 0.0434 

RMS LOS 0.086 95% Gimbal 0.125 

2 LOS 0.172 sec. 95% LOS 0.25 'LI 

115 

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PROPOSED BASELINE 

116 

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..SINET, SPECIAL HANDLING 

RATE - RATE CONFIGURATION 

ADVANTAGES 

MINIMUM VEHICLE TRANSIENT ERRORi 

NO ENCODER RISK 

COMMONALITY WITH DRIVE "A" 

GREATER FLEXIBILITY IN MAN-LOOP 

SERVO CONFIGURATION 

GREATER SERVO FLEXIBILITY FOR 

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LOW RATE CAPABILITY (0.010/sec) 

INCREASED RELIABILITY 

DISADVANTAGES 

HIGHER BEARING RISK 

117 

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RELEASE 1 JULY 2015 

.---StRELSPECIAL HANDLING 

POSITION - RATE CONFIGURATION 

ADVANTAGES 

LOWER BEARING RISK 

CAN HAVE LARGER NOISE IN DiA BUFFER 

DISADVANTAGES 

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LESS SERVO FLEXIBILITY 

ENCODER RISK 

LIMITED LOW RATE CAPABILITY 

LOWER RELIABILITY 

118 

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PROPOSED BASELINE 

ERROR ANALYSIS 

PITCH ROLL 

BEARING NOISE 0.045 0.0144 

GYRO NOISE 0.018 0.018 

D/A INPUT NOISE 0.022 0.022 

LOOP ELECT. NOISE 0.016 0.016 

RMS GIMBAL 0.0555 .0355 

RMS LOS 0.116 

2 LOS 0.232 sec. 

119 

SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

PROPOSED BACKUP 

PITCH ROLL 

BEARING NOISE 0.103 0.033 

ELECTRONIC NOISE 0.032 0.032 

QUANTIZING 0.53 max. 0.38 max. 

95% PROBABILITY GIMBAL 0.57 0.385 

95% PROBABILITY LOS 1.18 sec. 

19 BIT ENCODER PITCH 

20 BIT ENCODER ROLL 

max = 62 DEGREES 

60 RADIAN BANDWIDTH BOTH LOOPS 

120 

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RELEASE 1 JULY 2015 -11C4EL. SPECIAL HANDLING 

ENCODER ERROR 

1/4 BIT MAX. AMP 

2nd. HARMONIC ERROR CONTENT 

18 BIT 19 BIT 20 BIT 

ERROR RATE 

0.625 0.13 o/sec 0.065 o/sec 

0.3125 0.26 0.13 

0.156 0.52 0.26 0.065 o/sec 

0.078 1.04 0.52 0.13 

0.039 1.04 0.26 

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SLEW REQUIREMENTS 

RATE ERROR < 0.01 degrees/sec 

POSITION ERROR < 0.014 degrees 

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126 

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SLEW 

SAME TECHNIQUE AS MAIN TRACKING MIRROR 

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NO SATURATIONS 

MINIMUM STRUCTURAL EXICATION 

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SLAVING PERFORMANCE 

STRUCTURAL VIBRATION 26 u rad/sec 

TM SERVO NOISE 26 u rad/sec 

ATS SERVO NOISE 45 u rad/sec 

CREW ERROR 17 u rad/sec 

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153 

SPECIAL HANDLING 

DOCUMENTED FORM 

E.4 

Pq 

OF THRUSTOR PLUME, 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

4*IteREL SPECIAL HANDLING 

S/C A PDR ACTION ITEM STATUS 

I CONSIDERED COMPLETE AND CLOSED -- 37 TOTAL 

2, 3, 4, 8, 9, 11, 12, 14, 16, 18, 21, 22, 23, 32, 33, 35, 39 

42, 43, 46, 47, 48, 50, 51, 56, 57, 58, 59, 

68, 69, 71, 73 

60, 61, 62, 63, 65 

II HELD OPEN PENDING DESIGN CHANGE ACCEPTANCE -- 8 

#29 (SHROUD) 

#41 (18 BIT ENCODER) 

#44 (GIMBAL BALANCE WEIGHTS) 

#49 (SHROUD DRIVE) 

#52 (BRUSHLESS MOTOR) 

#54 (BRUSHLESS MOTOR) 

#72 (MANUAL REOPEN BLANKING SHUTTER) 

#75 (FMEA'S OF DESIGN) 

154 

SPECIAL HANDLING 
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S/C A PDR ACTION ITEM STATUS (CONT'D) 

III CONSIDERED UNSATISFACTORY WITH THE ENCLOSED WRITTEN 

COMMENTS TO S/C A -- 11 

#5 THE ACTION ITEM RESPONSE IS NOT COMPREHENSIVE. THERE IS 

LITTLE DETAIL AS TO HOW THE SUBCONTRACTOR WILL MINIMIZE 

DOWNTIME. APPARENTLY, THE DESIGN HAS NOT PROGRESSED TO 

THE POINT THAT SPECIFIC MAINTENANCE CONSIDERATIONS HAVE 

BEEN DEVELOPED. 

#6 THE RELIABILITY BLOCK DIAGRAM PROVIDED IS NOT ACTUALLY 

A RELIABILITY BLOCK DIAGRAM, PARTICULARLY CONSIDERING THE 

PRIME SAFETY FUNCTION OF THE MECHANISM. THE BLOCK DIAGRAM 

DOES POINT OUT SOME UNDESIRABLE FEATURES. FUNCTIONAL OR 

BLOCK REDUNDANCY SHOULD BE PROVIDED TO ASSURE PERFORMANCE 

OF THE BLANKING FUNCTION. THERE ARE SINGLE FAILURE ELEMENTS 

FOLLOWING THE LOGIC. 

SOME ADDITIONAL COMPLEXITY WOULD RESULT IN PROVIDING 

REDUNDANCY FOR THE PRIME FUNCTION; HOWEVER, CONSIDERING 

THAT THIS IS AN EQUIPMENT USED ONLY IN THE MANNED MODE, 

THE UNBLANKING FUNCTION COULD BE MADE MANUAL WITH WARNING 

PROVISIONS AND APPROPRIATE PROCEDURES, AND THEREBY ELIMINATE 

THE MOTOR. THE BLANKING FUNCTION IS FAR MORE IMPORTANT 

THAN THE UNBLANKING FUNCTION. 

IT IS RECOMMENDED THAT THE SUBCONTRACTOR PROVIDE REDUNDANCY 

FOR THE BLANKING FUNCTION TO THE EXTENT PRACTICAL AND 

THE RE-SET FUNCTION SHOULD BE MANUALLY PERFORMED. 

#10 THIS ACTION ITEM HAS NOT BEEN ANSWERED SATISFACTORILY. 

ITEK HAS LEFT THIS ITEM OPEN UNTIL THEY ESTABLISH A TOLERANCE 

BUDGET WHICH CAN YIELD AN MTF WHICH MEETS THE SYSTEM REQUIREMENT. THIS TOLERANCE BUDGET WILL THEN BE USED TO MAKE A 

WORSE CASE ANALYSIS. THUS, THIS ITEM CANNOT BE CLOSED 

UNTIL THE BUDGET IS ESTABLISHED AND THE ANALYSIS PERFORMED. 

#20 ACTION ITEM 20 DISCUSSED ALIGNMENT TECHNIQUES AND ACCURACY 

OBTAINABLE. IN A SUPERFICIAL WAY THE ACTION ITEM IS 

SATISFIED; HOWEVER, CONSIDERABLE JOINT EFFORT WILL BE 

REQUIRED TO GENERATE THE PROCEDURES NECESSARY TO RESOLVE 

THIS PROBLEM COMPLETELY. RECOMMENDATION IS FOR AN ICWG 

MEETING AFTER WE FIRST DEVELOP A FIRST CUT AT AN ALIGNMENT 

PROCEDURE. 

sPg_cjAL HANDLING 
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S/C A PDR ACTION ITEM STATUS (CONT'D) 

#25 ITEM #25 RESPONSE IS UNACCEPTABLE AS RECEIVED BECAUSE IT BEGGED 

THE SPECIFIC QUESTIONS TO WHICH IT WAS ADDRESSED. 

THE ALTERNATE DESIGNS MENTIONED WERE INFEASIBLE DESIGNS. THE 

INTENTION OF THE ACTION ITEM IS TO IDENTIFY FEASIBLE DESIGNS 

AGAINST WHICH THE MERITS AND PENALTIES OF THE PYROTECHNIC APPROACH 

CAN BE TRADED. INFEASIBLE CONCEPTS SEEM TO BE NO CONTENT AND 

DON'T PROVIDE MUCH OF A TRADE. 

THE TRADE STUDIES PRESENTED SEEM TO BE THE RESULTS OF STUDIES 

RATHER THAN THE STUDIES THEMSELVES, AS REQUESTED. THE ASSUMPTIONS, 

BASES, AND ANALYSES THAT YIELDED THE 0.5 INCH RELATIVE MOTION OF 

THE SCANNER WITH RESPECT TO THE SHROUD AND/OR LABORATORY MODULE 

AND THE 200 TO 300 LB. PIN FORCE ARE WHAT ARE REQUIRED BY THE 

ACTION ITEM. 

#38 AN ARBITRARY ALLOTMENT OF MECHANICAL NOISE BETWEEN FLEX CABLE 

NOISE AND BEARING NOISE WAS MADE. NO ANALYSES OR BACKUP DATA 

WAS PRESENTED TO JUSTIFY THE ALLOTMENTS. 

INTENT OF ACTION ITEM NOT SATISFIED. 

#40 SEE ATTACHED COPY 

#45 THIS ITEM WAS THE STRUCTURAL ANALYSIS OF THE TOTAL ACQUISITION 

SYSTEM STRUCTURE. THIS ACTION ITEM INCLUDED 14 ENCLOSURES. 

EACH ONE WILL BE DISCUSSED SEPARATELY. 

ENCLOSURE 1 ANALYSIS OF YOKE -- THIS ANALYSIS IS CONSIDERED 

TO BE ADEQUATE AND SATISFIES THE REQUIREMENTS. 

ENCLOSURE 2 ANALYSIS OF PEDESTAL -- THIS ANALYSIS IS CONSIDERED 

TO BE ADEQUATE AND SATISFIES THE REQUIREMENTS. 

ENCLOSURE 3 ANALYSIS OF PROTECTIVE SHROUD -- THIS ANALYSIS IS 

NOT ADEQUATE. THE ANALYSIS DWELLS ON A NUMBER OF 

FITTINGS AND FAILS TO SHOW THE ADEQUACY OF THE 

SHROUD ITSELF. NO ANALYSIS HAS BEEN PERFORMED 

TO DETERMINE IF THE SHROUD MEETS THE DESIGN REQUIREMENTS. IT IS REQUESTED THAT AN ANALYSIS OF THE 

SHROUD BE PERFORMED. THIS ANALYSIS SHOULD REFLECT 

THE SHROUD DESIGN AS OF THE FEBRUARY 1, 1968 TD 

MEETING. 

ENCLOSURE 4 ANALYSIS OF PRESSURE WINDOW -- THIS ANALYSIS IS 

CONSIDERED TO BE ADEQUATE AND SATISFIES THE REQUIREMENTS. 

s ietAt HANDING 
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-1-EGRET- SPECIAL HANDLING 

S/C A PDR ACTION ITEM STATUS (CONT'D) 

#45 (CONT'D) 

ENCLOSURE 5 

ENCLOSURE 6 

ENCLOSURE 7 

ENCLOSURE 8 

ENCLOSURE 9 

ENCLOSURE 10 

ENCLOSURE 11 

ENCLOSURE 12 

ANALYSIS OF OBJECTIVE LENS ASSEMBLY 

ANALYSIS OF FIRST LOW POWER ASSEMBLY 

ANALYSIS OF SECOND LOW POWER ASSEMBLY 

IN THE ABOVE ACTION ITEMS (5, 6 AND 7) MUCH ANALYSIS 

IS PERFORMED ON THE LENS ELEMENTS. THE LENS 

RETAINERS, RINGS, SPACERS, ETC., ARE ADEQUATELY 

ANALYZED, BUT THE STRUCTURE WHICH TIES THE LENS 

SYSTEM TOGETHER (THE TELESCOPE TUBE) IS NOT ANALYZED 

TO ANY EXTENT. IT IS FELT THAT THIS ANALYSIS IS 

OF THE UTMOST IMPORTANCE AND SHOULD BE PERFORMED 

AS SOON AS POSSIBLE. 

ANALYSIS OF INTERNAL FOLD MIRROR -- THE TITLE OF 

THIS ENCLOSURE IS DECEIVING. THE ENTIRE ANALYSIS 

DOES NOTHING BUT ANALYZE THE DUST COVER OVER THE 

INTERNAL FOLD MIRROR ACCESS HOLE. IN NO WAY IS 

THE MIRROR AND THE MOUNTING STRUCTURE ANALYZED. 

THIS SHOULD BE DONE BEFORE THIS ENCLOSURE IS 

CONSIDERED COMPLETE. 

ANALYSIS OF PECHAN PRISM ASSEMBLY -- THIS ANALYSIS 

IS CONSIDERED TO BE ADEQUATE AND SATISFIES THE 

REQUIREMENTS. 

ANALYSIS OF RETICLE ASSEMBLY 

ANALYSIS OF ZOOM ASSEMBLY 

ANALYSIS OF ZOOM CYLINDER 

ENCLOSURE 13 ANALYSIS OF EYE PIECE 

ENCLOSURE 14 ANALYSIS OF FILTER ASSEMBLY 

OF THE FIVE ABOVE ACTION ITEMS, FOUR OF THEM CONSIST 

ONLY OF A DETERMINATION OF THE ASSEMBLY WEIGHT. 

THE ANALYSIS OF THE ZOOM CYLINDER IS MORE COMPLETE 

AND MEETS THE REQUIREMENTS, THE REMAINDER BEING 

INADEQUATE, SINCE, IN ESSENCE, NO ANALYSIS WAS 

PERFORMED. 

ON THE WHOLE, THIS ACTION ITEM IS INADEQUATE. IN 

MOST INSTANCES, THE ANALYSIS COMPRISES VERY DETAILED 

ANALYSIS OF FITTINGS, ETC., BUT THE IMPACT OF THESE 

157 

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S/C A PDR ACTION ITEM STATUS (CONT'D) 

#45 (CONT'D) 

ITEMS ON THE TOTAL STRUCTURE IS NOT IN ANY WAY DETERMINED. THIS 

IS ESPECIALLY TRUE IN THE TELESCOPE WHERE NO ANALYSIS WAS SHOWN 

ON THE TELESCOPE STRUCTURE ITSELF. THERE WAS NO ANALYSIS SHOWN 

ON THE TELESCOPE ELBOW WHICH IS FELT TO BE A CRITICAL ITEM. 

ALSO, NO ANALYSIS IS PRESENT ON THE TRACKING MIRROR BEZEL. 

THE ANALYSIS OF THE GYRO MOUNTING WOULD BE OF MUCH INTEREST. 

THERE WAS ALSO NO ANALYSIS SHOWN ON THE EXTERNAL FIXED FOLD 

MIRROR. IT SHOULD BE NOTED THOUGH THAT THE ANALYSIS OF THE YOKE 

AND PEDESTAL WAS VERY GOOD AND SHOULD BE USED AS A BASIS FOR 

FURTHER ANALYSIS. 

#67 THE ACTION ITEM RESPONSE APPEARS TO BE A REASONABLE PRELIMINARY 

FMEA ON THE LOW POWER CHANGER. THIS RESPONSE IS RELATED TO 

THAT ON ACTION ITEM #70. 

#70 THERE IS LITTLE DIFFERENCE IN RELIABILITY AS INDICATED BY THE 

PREDICTIONS FOR THE 4 POWER CHANGER CONFIGURATIONS. THE SELECTED 

CONFIGURATION APPEARS TO BE REASONABLE WITH THE POSSIBLE EXCEPTION 

OF THE SPIROID GEAR ARRANGEMENT. IT IS POSSIBLE THAT THIS COULD 

INTRODUCE UNDESIRED FORCES WHICH WOULD BE A PROBLEM. DETAILED 

MECHANICAL EVALUATION IS NECESSARY TO FURTHER EVALUATE THE 

SELECTION. 

#74 SEE ATTACHED COPY. 

158 

----Sleihrg---SPECIAL HANDLING 
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RELEASE 1 JULY 2015 -1-EGREL, SPECIAL HANDLING 

IV STILL BEING WORKED AT S/C A AND/OR GE -- 8 

ITEMS TO BE RECEIVED FROM S/C A 

26 (WEIGHT REDUCTION TRADE STUDIES) 

34 (DYNAMIC ANALYSIS) 

64 (VIGNETTING) 

66 (DYNAMIC ANALYSIS) 

ITEMS BEING REVIEWED BY GE 

1 CRITICAL PARTS LIST 

7 COMPLIANCE TO MIL-S-38130A AND MIL-STD-470 

36 BEARINGS -- TEST PLAN 

37 BEARINGS -- HOUSING 

159 

SPECIAL HANDLING 
PMPE Staff 

P. Martin 

V. Ries 

D. Smith (4) 

p, rnotv■ eekGEK 

ST'EVAL HAN 

160 FO 'M 1020 H REV. 19-65) 

n 

n 

n 

n 

n 

1 MO. 

3 Mos. 

6 MOS. 

M05. 

NRO APPROVED FOR 

RELEASE MINIM ELECT 

MISSILE AND SPACE DIV 

MAMMA 

PROGRAM INFORMATION REQUEST/RELEASE 

rraom Leon Brown, Manager 

IParts and Applications Engineering 

Room 133, Radnor, Ext. 460 

DATE SENT DATE INFO. NMI= 

•CLAZS. LIR. 07-TRATIOZ1 PROGRAM 1SEQUENC:E NO. REV. UM. 

15 PE IAL, HA D1.11,N 007 

PIR NO. 

USE "O" FOR CLASSIFIED AND "U" FOR UNCLASSIFIED 

To D. Smith, Development Engineer 

Alpha Subsystem 

Room 126, Radnor 

PROJECT AND REQ. NO. REFERENCE DIR. NO. 

2/21/68 

SOSJECT 

ACTION ITEM NO. 74 

INFORMATION REQUESTED/RELEASED 

The list of materials contained in the subject action item has been reviewed. 

This list indicates that the subcontractor has not conformed to the Selected 

Materials List for the Lab Module - DR1115. Materials have been included 

which will require testing to assure meeting the program requirements. Specific 

comments are: 

Manufacturer Material Designation Remarks 

Sanders Mylar and Kapton Flexprint Kapton-Satisfactory 

Mylar-Unacceptable 

Shell Oil Apiezon Lubricant Requires Testing 

Dow Corning White Thermatrol Paint 92-0007 Requires Testing 

Mystic Tape Pressure Sensitive Al Tape 7042 Acceptable 

Bendix Glass Reinforced Epoxy MI7.-C-26411 Note 1 

Cannon Glass Filled Thermosetting MDB1-37SH Note 1 

Gudebrod Nylon Lacing Tape MIL-T-713A Acceptable 

Aeroflex Potting Compound Requires Testing 

Beckman Lubricant 01 • Note 2 

Integrated Energy Absorbent Sponge Requires Testing 

Dynamics 

Bacon Epoxy LCA-4 Requires Testing 

Industries 

Dupont Mylar Shim 4*. Note 2 

3M Paint 3M-3101 Requires Testing 

3M016 

n 5... 

n12 MOS. 

R moo. 

I-IDONOTOtSTROY 

RETENTION REQUIREMENTS 

COPIES FOR MASTERS FOR 

::*AGE NO. 

L 3 

LING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

PIR 7L73-007 

Page 2 

Manufacturer Material Designation Remarks 

PK Menses Marking Ink .. Note 2 

H. B. Fuller Epoxy Resin -- Note 2 

GE RTV Silastic -- Cannot Identify. 

GE makes RTV but 

not Silastic 

Microseal Lubricating Compound -- Requires Testing 

Corp. 

Armstrong Adhesive A-6 Requires Testing 

Dow Corning Grease FS1291 Note 2 

Isydon Eng. Phenolic Retainer KA42AH Requires Testing 

Dupont Nylon MIL-P-17091, Type 1 Requires Testing 

GE RTV 103 -- Requires Testing 

3M Cement EC1022 Requires Testing 

GE Silicone Sponge Rubber SE547 or AMS3195 Requires Testing 

Chemical WOK 402 -- Requires Testing 

Develop. Corp. 

3M Paint Primer 3101-C10 Requires Testing 

AMP Nylon FM10001 Requires Testing 

GE RTV30 -- Requires Testing 

161 

'"1"ft-lift SPECIAL HANDLING 
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PIR 7L73-007 

Page 3 

NOTE 1: These materials are parts of connectors. Connectors will require 

prior approval as parts in accordance with DR1110. Because of the 

complexity of the connectors, when testing is required, it should 

be done on completed units. 

NOTE 2: Requirements for these items are waived due to the small quantity 

of material present. Waiver applies to the application specified 

only. 

It is strongly recommended that the subcontractor review the latest issue of 

DR1115, as a potential source for materials presently approved. This could 

result in appreciable reduction in the amount of testing required. Future 

contacts on the approval of materials should be made to G. R. Bretts, Manager, 

Materials Engineering at Building A, Room 20A35. 

162 

SPECIAL HANDLING 
ROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

TO: D. Snith 

!r.024: L. W. Goons 

SULU& I& Action Item UP. 40 

The action it responee received may be consid:!red compliant. It in 

not sotisfnctory, honnver. Thin ;sound.; nonethat inconeietent, but unit it 

means is that they eppenently supplied all the infonontion they had end 

that this information is de one to assuna they nre leoking in technical 

depth end enperience in thin pnnticulor erea. 

They have obviously ypnnt C0.23 7 tiee inveztigeting the flexible cable 

harnenono and hove indiented several "novel" Ulnae. They do not indiccte 

if thoce "novel" ieB;v) hnve been used before in servo :d epplicatiens requiring 

los torquee dioturbnncee. They do cention COM3 pant onperinace with the 

"roll-elong" cable, but Co not olsbereZe. 

A great deal of enelynie could hove (and perhe2n should hove) been done 

to analyze the torque levels versus position, rnd the pertunbation which 

might occur. nethennticni modelc could have Leen coeatructed with nneumad 

conditions such as friction end contnct conditiene whera the cable might 

touch the containing wells. Calculations of the effect of "g" loadings 

should have been mnda. 

The test e23Crip;',10n is COO vague. That spocdo will they run, rad what 

frequsncy responne ced rnnolufion tlet cqui.n,an h,vn? Vow will they 

factor this into their syat-m to nrztve et rezIon,n 'a:to degraZaticn? Their 

definition of toi:qu-J cn:.,turb,aca and '223 not slv:a. 

Inaufficient infoon'tion is given el thn pitch confiLunntion. It 

would appear that the annnnInvent they selectod is not optinum. Simpler 

configuretionn might suffice end could o!fer edventngen. 

It is not knonn nhethen they intnni to cable the entire device with 

one continuous run of flan cnble, Min could linit their e2Zi311 poenibilitieo. 

In any event, they do not inetcata tha effect on to-nqua of end rentraints, 

e.g., clans, conn.n:tionn, at-4. 'Toile the torqn dtstunbnocen (es opposed 

to static restraint) -neuld be difficult to cnlculn1n2, they could be eetimated 

and empirically verified—if specifienlly lco'ned for. 

As an exanple of a eonsnhnn batter reply to a cimilar action item, 

I refer you to tha raeponse given by ::.ollsnnn to their Star Tracker FOR 

action item on this subject. Whilo not fully entia.factory, it does 

indicate some aneae nhere fuscher investigation could be performed. 

A 

cc: 

W. J. Male/ 

L. FotkoEny 

G. R. Qa-liui 

S. B. Folks 

163 

HANDUNG 

e 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 --lfeitg- SPECIAL HANDLING 

ATS & VDP OPTICAL ANALYSIS (QUESTIONS ONLY) 

4. QUESTION: Page 2-76 - The correction of the mathematics is 

questioned (706.5 - 708). 

ANSWER: The equations on page 2-76 are correct; however, an 

error occurred in the numerical evaluation. As a 

simplification the slant range may be expressed as 

- - k [ 

where 

t 

,...L 

and 

L 

The following values may be determined 

H B d flat 

n mi. deg. Correction n mi n mi 

80 70 .087 234 254 

230 70 .25 673 875 

Page 2-76 then should read: 

The slant range at 70° and 80 n mi goes from 234 n mi 

to 254 n mi on a curved earth, on 8.7 per cent increase. 

At 230 n mi altitude at 70° the slant range is 673 n mi 

for a flat earth and 875 n mi on a curved earth which 

is a 25 per cent increase. At 80 n mi altitude the 

8.7 per cent increase will increase the defocus 

error by approximately 8.7 per cent and will then 

SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 -.-11414-1-. SPECIAL HANDLING 

amount to 0.0033 in. At 230 n mi. altitude, even with 

the 25 per cent increase, the defocus amounts to only 

0.0031 well within eye accommodation as is the worst 

case at 80 n mi. 

165 

c!-IFC1 MitNG • 
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5. QUESTION: What are the effects on the adjustments on the 

reticle of the Acquisition Optics? 

ANSWER: This is covered in detail on page 2.74, Section 

2.1.4.5 - "Focus" of the Engineering Analysis 

Report. Briefly, the defocus due to this cause 

will be 0.14 diopters. The depth of focus of 

the eye is 0.5 diopters. The depth of focus 

of the eye is sufficient to compensate for 

this defocus. 

166 

--I-ER-EL SPECAL H.AMLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 -S-EG-RE-T- SPECIAL HANDLING 

17. QUESTION: What are the focus characteristics of the peripheral 

display lights relative to the scene? 

ANSWER: The peripheral display will be placed in such a position 

in relation to the aerial image so as to require minimum 

eye accommodation. 

18. QUESTION: Are GE/Sub following on these recommendations? 

(Tolerances on curvature radii; triplet instead of 

doublet). 

ANSWER: GE and Subcontractor "A" are following up recommendations. 

(1) Doublet radii should be selected such that all 

tolerances are plus or all tolerances are minus 

on a given assembly. 

(2) The triplet will not be used. Latest estimates 

on weight indicate an increase of 10 lb. each 

for incorporation of the triplet. System 

performance can be met with the doublet. 

A 

167 

SPEC AL rIANDUNG 
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19. QUESTION: The results contained in Table 2.1 - 3 indicate a 

definite need for corrective action. Resolution 

provided in some cases worse than using a window. 

ANSWER: We have no specification for off-axis performance. 

The need for improvement is not apparent. We will 

provide Itek analysis of this problem as soon as it 

is available. We would be interested in seeing 

Aerospace analysis using CDC6600 computer program 

when results are available. 

20. QUESTION: What about field curvature off axis resolution trade off? 

ANSWER: Fully discussed in Section 3.6 P 201 of EAR. 

21. QUESTION: No consideration was given in EAR on tilting and 

decentering tolerances. 

ANSWER: That is correct. This problem was covered extensively 

in Itek's PDR report, Section 3.6.5, Page 3.6 - 84. 

Fabrication and alignment Tolerances. No attempt was 

made to duplicate work in EAR that was adequately 

covered in Subcontractor's PDR Report. 

22. QUESTION: Discuss tests which will be used to verify optical 

performance of the flight hardware. 

168 

"IfeR-F SPECIAL HANDLING 
NRO APPROVED FOR 

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r. 

(22) ANSWER: Test used to verify performance have not been 

described to date. The philosophy used in preparing 

these test plans will be to provide detail tests 

during manufacture and assembly to insure that the 

performance curve provided in the Itek PDR Report 

is in fact the "worse case" that will be accepted 

for flight use. 

169 

---IfreHT,. SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 -1E-RE-T- SPECIAL HANDLING 

52a. QUESTION: What is status of your spec to subcontractor. 

ANSWER: The specification EC331B has been negotiated with 

Itek through Section 3. In Section 4, there are two 

items that have not been resolved. Both involve 

environmental test on the scanner, fixed fold, and 

window relative to salt fog, rain, propellant 

compatability, explosive atmosphere, and wind. 

These items are currently being negotiated. 

SPECIAL HANDLING 
NRO APPROVED FOR 

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ANSWER (52b continued) 

(10) 3.1.1.1.21 Mechanical stops on zoom 

(11) 3.1.1.1.22 Changed 5° obscuration to 3° 

Changed 70 lights to 35 lights added TBD 

brightness 

(12) 3.1.1.1.23 Blanking fail safe 

(13) 3.1.1.1.23 Manual Unblanks of FOV 

(14) ..1.:.1.1.25 " Leakage Requirement - 100 cc/day/inch of 

Seal. Operational 5 hours after launch 

operational 3 hours after pressurization. 

(15) 3.1.1.2.1 References defining scanner axis tolerance 

Change from + 0.5 arc minutes to + 0.25 arc 

minutes. 

(16) 3.1.1.2.3 Field of View 60 degrees 

(17) 3.1.1.2.4.1 Blanking Override 

(181 Reliability for Peripheral Display added. 

(19) 3.1.2.3 Useful Life 

Prism Positionings 12,000 

Shroud Door 500 

(20) 3.2.1.1.4 Operating voltage and ripple, and power interrupt 

(21) 3.3.1.1 Weight 166 

(22) 3.3.1.2 Power 105 Pulse 110 (60MS) 

(23) 3.3.1.3 Safety Factors added per DR1100 

171 

lefig. SPECIAL InANDL 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 "lit-RE--T. SPECIAL HANDLING 

52b. QUESTION: Is "A" Spec different than one included in Volume 1 of 

the "A" PDR? 

ANSWER: Yes. Spec in Vol. 1 of "A" PDR was based on EC331B. 

Changes from EC331B are outlined as follows: 

(1) 3.1.1.1.1 Change tolerance on max. mag. 127X 

(2) 3.1.1.1.2 Resolution 

Old 3.3 ft. per line pair ground resolution 

on orbit. 

New 3.3 ft. per line pair ground resolution 

(analysis) 

3.0 ft. per line pair ground resolution simulated 

in laboratory (demonstration) 

(3) 3.1.1.1.3 Maximum vignetting 60% over entire scan field 

(4) 3.1.1.1.7 Change scanner gimbal inertia from .12 to .08 

and .20 to .23. 

(5) 3.1.1.1.9 Changed lower rate from .14 deg/sec to .10 

deg/sec (max. 40 deg/sec). 

(6) 3.1.1.1.11 Add stops to pechan prisms 

(7) 3.1.1.1.12 Space allocation for cue mechanisms only 

(8) 3.1.1.1.19 Range of focus + 3.5 to - 2.5 diopters added 

(9) 3.1.1.1.20 Add resolution at four magnification points. 

Resolution 3.3 6.6 13.2 26.4 

Magnification 127.0 63,5 31.75 15.88 

172 

SPECIAL HANDLING 
NRO APPROVED FOR 

REL 7` • SWAY P3 b c ontinu 

(24) 3.3.1.4 

(25) 3.3.1.5 

(26) 3.3.1.2 

SPECIAL HANDLING 

Steady state design load factors added 

Wiring (Kapton) added 

Cleanliness added 

Surface: Per ST9802 Level 500 

Packaging: Maintain ST9802 line 500 

Expansion of Itek Error Allocation Per 3.1.1.1.2 

3.3 Ft. Static (.152 A ) 

External 

(.0854A ) 

3.0 Ft. (.1145 X ) 

4/ 

Static Bench Test 

Includes mirrors and 

optical window 

(glass qual- fab. 

tolerances, etc.) 

On Orbit .„(.10/k) 

Thermal (.095 X) Other (.030)) 

release) 

(launch 

Internal environment) 

(.042).) 

/1 

window 2 mirrors 

(.070A) (.035A) 

53. QUESTION: Discuss any changes which are currently under negotiations? 

This information is covered in the answers to 52a and 52b. 

173 

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SUMMARY OF ACQUISITION 

SUBSYSTEM PERFORMANCE PREDICTION ANALYSIS 

- STATIC PERFORMANCE 

SUMMARY OF ANALYSIS IN SECTION 2.1.3 OF EAR REPORT 

RESOLUTION AS A FUNCTION OF INPUT CONTRAST RATIO 

STATISTICAL PREDICTION OF SYSTEM RESOLUTION 

- DYNAMIC PERFORMANCE 

SUBSYSTEM PERFORMANCE AS A FUNCTION OF HALF-AMPLITUDE 

L.O.S. JITTER (MONOTONIC) 

- DISCUSSION OF JITTER EXPERIMENT AT SUBCONTRACTOR ALPHA 

- FUTURE WORK 

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ALLOWABLE JITTER FROM ECP 17 TO GE-AVE CLI SPEC. 

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- REFINE PRESENT ESTIMATES OF NOMINAL ON-ORBIT PERFORMANCE 

- COMPLETE WORK ON JITTER EXPERIMENT APPARATUS 

- ESTABLISH AN AVERAGE RESOLUTION THRESHOLD CURVE FOR THE CREW 

- EXPERIMENTALLY EVALUATE THE EFFECT OF MONOTONIC JITTER ON 

RESOLUTION AND COMPARE WITH ANALYTICAL STUDIES 

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- EXPERIMENTALLY AND/OR ANALYTICALLY EVALUATE THE EFFECT OF ACTUAL 

LOS. JITTER ON SYSTEM PERFORMANCE 

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187 
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DRIVE K BEARINGS 

PRELIMINARY DESIGN REVIEW 

MARCH 6, 1968 

188 

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SCOPE 

o REQUIREMENTS DEFINITION 

o STATUS ACTIVITY 

o RESULTS TO DATA 

BEARING DATA - BARDEN TASK IA . 

LUBRICATION TESTS 

o ACTIVITIES IN PLANNING 

o SUMMARY 

189 

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STATUS OF ACTIVITY 

o PRELIMINARY DESIGN - COMPLETED BY SUBCONTRACTOR. 

- CONTINUING REVIEW BY G.E. 

o BEARING TESTING - INITIAL TESTS COMPLETE - BARDEN IA. 

- SECOND SERIES OF TESTS UNDER:.AY BY SUE. 

- G.E. DUBE TEST DATA IS APPLICALE. 

- EVALUATE NECESSARY BEFORE ADDITICL 

:EST PLAN1ING. 

o BRASS LOARD TESTS - FIXTURE UNDER DESIGN AT G.E. 

- COCKING AND CLEANLINESS AR: CONSIDERATIONS. 

o "CUSTOM STRIPPED" F-50 SEEMS LEST CHOICE ACAIN. 

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PSD ALLOCATION 

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PSD DATA 

10 LOG PSD 

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(1.1) 

= 1.17 x 8°/SEC = 0.94 Hz LUBE . 

(0.91) 

SPEC19jAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SECRET SPECIAL HANDLING 

2=0R..'ANCE 

o ESTIMATE OF HARDWARE • 

BARDEN IA DATA (.316 X 10-4 IN.OZ2/Hz) -65db 

FOUR BEARINGS ON SHAFT = 4 X IS +12db 

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(GUESS) 

-25db 

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194 

SPEC1P-A HANDLINS 
NRO APPROVED FOR 

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ACTIVITIES IN PLANNING 

o CORRELATION OF BARDEN DATA WITH G.E. DATA TO: 

RESOLVE SAMPLING UNCERTAINTIES. 

PROVE VALIDITY OF RESULTS. 

ESTABLISH AVAILABILITY OF BEARING. 

EVALUATE EFFECTS OF COCKING. 

EVALUATE SUBSTITUTION OF SPACE LUBRICANT. 

EVALUATE EFFECTS OF TORQUER SIDE FORCE. 

o INVESTIGATE THE PERFORMANCE EFFECTS OF: 

INSTALLATION (MISALIGNMENT, SIDE FORCE). 

LOADS (FRETTING, BRINNELLING). 

o DIRECT SUBCONTRACTOR EFFORTS IN AREA OF: 

INSTALLATION. 

CLEANLINESS. 

o INVESTIGATE TEMPERATURE EFFECTS ON: 

CLEARANCES AND LOADS. 

LUBRICANT. 

CREEP BARRIER. 

SEALS. 

TORQUE RIPPLE. 

TORQUE. 

SPiethAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 --1-EMET- SPECIAL HANDLING 

SUMMARY 

o "K" BEARINGS ARE IN THE EARLY DESIGN STAGES. 

o PRELIMINARY TEST DATA INDICATES ACCEPTABLE PERFORMANCE 

AVAILABLE FROM HIGH QUALITY PRECISION INSTRUMENT 

BEARINGS. 

o G.E. WILL EMPLOY "A" EXPERIENCE TO DIRECT SUBCONTRACTOR 

INSTALLATION PARAMETER. 

o LUBRICATION TEST DATA IS DIRECTLY APPLICABLE. 

o THE ERROR ALLOCATION SEEMS REASONABLE IN TERMS OF 

PRELIMINARY TEST DATA - SUBSTANTIATION MUST BE 

ACCOMPLISHED. 

o BEARING S.O.A. - FROM PRELIMINARY DATA - SEEMS BETTER 

ON THIS SIZE BEARING THAN ON THE "A" BEARINGS. 

o MAJOR PROBLEM - EFFECT OF TEMPERATURE RANGE ON PERFORMANCE. 

S*CIAL HANDUNG 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 ---ifeRfr-SPECIAL HANDLING 

SUPPLEMENT - page 1 - 

DRIVE K TEST PLAN 

o SUB A 

TESTING TO ESTABLISH TECHNICAL STATUS 

DONE IN ONE MONTH 

ANALYTICAL WORK ON TEMPERATURE PROBLEM 

o G.E. 

TESTING TO ESTABLISH DESIGN POINT FEASIBILITY - DONE 

(BARDEN IA AND LUBRICATION TESTS) 

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o DEVELOPMENT TESTS 

(PRELOAD, MISALIGNMENT, TEMPERATURE, SURFACE 

MEASUREMENTS) 

o VERIFICATION TESTS 

(FULL AXIS TESTS) 

o TEST SPECIMEN AVAILABILITY 

o 440C INSTRUMENT GRADE BEARINGS - JUNE - JULY 

o FIXTURE AVAILABILITY - SIMILAR 

197 

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SUPPLEMENT - page 2 - 

ASSESSMENT OF CURRENT SUB A 

TEST PROGRAM 

o COMPETENT SUBCONTRACTOR WITH COPY OF MIT GYRO BEARING 

TEST EQUIPMENT DOING TESTS. 

TEMPERATURE ANALYSIS WORK STARTED 

100°F !;'f 10 LBS OF PRELOAD 

46°F 1,=Z 5 LBS OF PRELOAD [ 

UNCHECKED 

SUB A NUMBERS 

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G.E. DATA. 

o ERROR ALLOCATION STILL SEEMS REASONABLE. 

o SUB A WANTS TO DEVELOP CAPABILITY TO TEST BEARINGS FOR 

ACCEPTANCE - NEEDS ABILITY TO TEST AND UNDERSTAND 

RESULTS. 

o CLEANLINESS CRITERIA HAS BEEN TRANSMITTED TO SUB A. 

• 

SIOCIAt HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

THERMAL DESIGN 

o DESIGN BASELINE 

A. ENVIRONMENT - EXTERNAL 

1. ON-ORBIT 

a. SOLAR, EARTH & ALBEDO HEATING 

b. FREE MOLECULAR HEATING 

c. ACTS THRUSTER FIRING 

d. VACUUM 

e. MISSION MODULE & RADIATOR TEMP. VAR. 

(-100°F to +210°F) (-60°F to +80°F) 

2. ASCENT 

a. AERODYNAMIC SHROUD REACHES A PEAK TEMPERATURE 

g1000°F INN 120 SEC. 

b. ON-ORBIT SHROUD REACHES PEAK TEMPERATURE ;;?140°F 

c. AFTER EJECTION OF AERO-FAIRING ON-ORBIT SHROUD 

SUBJECT TO SIGNIFICANT MOLECULAR HATING 

- STAG. HTG. RATE .7 Btu/sec.-ft 

MAX. EST. TEMP. = 320°F (FLAT PLATE) 

B. INTERNAL ENVRIONMENT 

1. PRESSURIZED COMPARTMENT 

2. THREE DIFFERENT REGIONS 

a. LIVING CREW AREA - 66°F-80°F 

ON-ORBIT b. CONSOLES - 50°F-150°F 

c. ANNULAR SPACE BETWEEN BIRDCAGE & PRESSURE 

SHELL - 65°F-80°F 

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o INSULATION CONFIGURATIONS 

A. MULTILAYER INSULATION 

1. ALUMINUM FOIL & TISSUGLAS - 900°F 

2. ALUMINIZED MYLAR - 300°F 

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TEMP. 164°F TEMP. 1000°F 

211 

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C. SINGLE SHIELD 6 .07 

S VI? MAX. 240°F PEAK 600°F 

INTERNAL< 355°F SHROUD < 800°F 

TEMP .525°F TEMP. 1000°F 

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221 

---SteRETt- SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 4SICALL SPECIAL HANDLING 

o AEDC PLUME TEST 

TEST SPECIMEN ORBIT ADJ. SIM. ATT. CONT. SIM. 

THERMAL CONTROL .L.TO FLOW - TO FLOW - 

COUPONS SEE NOTE 1 INCORRECT POSITION 

FLUSH MT'D. SAMPLE fl TO FLOW - 8 SAMPLES 

- INCORRECT POSITION 5 QUARTZ DISKS WITH NONREFLECTING MgF COATING 

3 - Al +SO 

FRONT FACE SEE NOTE 1 

CALORIMETER 

HEAT FLUX PROBE SEE NOTE.2 

NOTE 1 - CANNOT BE TESTED UNLESS ADD'TL. TESTS ARE MADE 

AFTER JUNE 30th, OR UNLESS DACo HORIZON SENSOR 

HEAD IS DELETED FROM TESTS 4 & 5 OR DACo 

MONOPOLE GROUND PLANE ANTENNA DELETED FROM 

TEST 6. 

NOTE 2 - CANNOT BE TESTED UNLESS ADD'TL. TESTS ARE MADE 

AFTER JUNE 30th, OR UNLESS ONE OF THE GE OR 

DACo T/C COUPONS ARE DELETED OR ANTENNA TEST 

DELETED. 

222 

4*Sle-RiL SPECIAL HANDLING 
SPECIAL HANDLING 

• MAJOR DESIGN PROBLEMS 

COATING SELECTI

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DEGRADATION 

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?-1 

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SHROUD SHA

PE OPTIMIZATION 

INSULATION CONF

IGURATION OPTIMIZATION 

I 

SHROUD MATERIAL SELECTION 

44 

223 

YAK( SPECIAL •HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 '%1EGREL SPECIAL HANDLING 

ATS STRUCTURAL ANALYSIS 

STRUCTURAL ANALYSIS WAS PERFORMED ON THE FOLLOWING COMPONENTS: 

1. TELESCOPE 

2. SCANNER 

3. SHROUD 

PURPOSE OF ANALYSIS 

1. DETERMINE IF ITEK'S STRUCTURE IS CAPABLE OF WITHSTANDING 

POWERED FLIGHT AND ON-ORBIT LOADS. 

2. USE THE RESULTS OF THE ANALYSIS TO MAKE RECOMMENDATION ON 

DESIGN CHANGES TO ITEK. 

3. DETERMINE THE DEGREE OF OPTIMIZATION OF ITEK'S STRUCTURE 

AND USE THE RESULTS TO RECOMMEND WEIGHT SAVINGS TO ITEK. 

4. PERFORM ALIGNMENT STUDIES USING INFORMATION OBTAINED FROM 

THE ANALYSIS. 

224 

EE_ SPECIAL HANDLING 
THE MODEL USED IS THE FOLLOWING: 

PWR. GROUP _ 

ZOOM ASSEMBLY 

SHEAR TIE 

_ TRANSITION ASSEMBLY 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 -11C-R-EL SPECIAL HANDLING 

ATS STRUCTURAL ANALYSIS 

STRUCTURAL ANALYSIS OF THE ATS TELESCOPE 

ANALYSIS WAS PERFORMED USING GE STRUCTURAL COMPUTER PROGRAMS. A STRUCTURAL 

MODEL WAS MADE USING ITEK DRAWINGS. THE FOLLOWING ASSUMPTIONS WERE MADE 

IN CONSTRUCTION OF THE MODEL: 

1. THE CONNECTION BETWEEN THE OBJECTIVE END AND THE PENETRATION FITTING 

WILL NOT TRANSMIT TORSIONAL LOADS. 

2. THE TELESCOPE IS MADE OF BERYLLIUM AND ALUMINUM. 

(NOTE: IN DEFLECTION STUDIES, THE TELESCOPE WAS CONSIDERED TO BE 

ALUMINUM ONLY). 

3. THE WEIGHT OF THE TELESCOPE IS 81.10 LBS. 

4. THE LOADING USED WAS OBTAINED FROM DAC BIRDCAGE LOADS MODIFIED TO 

TRENDS SHOWN BY THE 3A LOAD CYCLE. 

PECHAN ASSEMBLY 

EYE PIECE 

THE RESULTS OF THE TELESCOPE STRUCTURAL ANALYSIS ARE: 

1. THE TELESCOPE WILL WITHSTAND THE LOADINGS IT IS SUBJECTED TO. 

2. THE WEIGHT OF THE TELESCOPE STRUCTURE CAN BE REDUCED. 

3. THE MINIMUM MARGIN OF SAFETY IS +0.46 (LIMIT) WHICH IS FOR CRIPPLING 

OF THE SHEAR TIE. ALL OTHER MARGINS ARE HIGH. 

225 

SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 Iferila SPECIAL HANDLING 

ATS STRUCTURAL ANALYSIS 

STRUCTURAL ANALYSIS OF THE ATS SCANNER 

THE ANALYSIS WAS PERFORMED USING GE STRUCTURAL COMPUTER PROGRAMS. THE 

STRUCTURAL MODEL WAS MADE USING ITEK DRAWINGS. THE FOLLOWING ASSUMPTIONS 

WERE MADE IN THE CONSTRUCTION OF THE MODEL AND SUBSEQUENT ANALYSIS: 

1. THE SCANNER IS MADE ENTIRELY OF BERYLLIUM 

2. THE WEIGHT OF THE SCANNER IS 70.75 LBS. 

3. WORST CASE INERTIA MAKE-UP WEIGHT WAS USED 

4. THE MIRROR-BEZEL COMBINATION IS A RIGID BODY 

5. THE LOADING USED WAS OBTAINED FROM DACO BIRDCAGE LOADS MODIFIED TO 

TRENDS SHOWN BY THE 3A LOAD CYCLE. ROLL HOUSING 

THE MODEL USED IS AS FOLLOWS: 

PEDESTAL 

ROLL SHAFT 

PITCH MOTOR 

\\44, MIRROR GYRO 

YOKE 

PITCH ENCODER 

THE RESULTS OF THE SCANNER STRUCTURAL ANALYSIS ARE AS FOLLOW: 

1. THE SCANNER IS CAPABLE OF WITHSTANDING THE LOADS IT WILL BE SUBJECTED TO. 

2. THE MARGINS OF SAFETY ARE HIGH. 

3. A DEFINITE WEIGHT REDUCTION POTENTIAL EXISTS. 

226 

SPECIAL HANDLING 
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ATS STRUCTURAL ANALYSIS 

STRUCTURAL ANALYSIS OF THE PROTECTIVE SHROUD 

THE ANALYSIS PERFORMED WAS A HAND ANALYSIS WITH THE SPECIFIC PURPOSE 

OF DEMONSTRATING THAT A SHROUD WHICH WEIGHS APPROXIMATELY 14 LBS. IS 

FEASIBLE. THE ASSUMPTIONS MADE ARE AS FOLLOWS: 

1. THE SHROUD WILL CONFORM TO THE SAME ENVELOPE AS THE ITEK PDR DESIGN SHROUD. 

2. THE SHROUD WOULD UTILIZE BERYLLIUM, MAGNESIUM OR FIBERGLASS AS STRUCTURAL 

MATERIALS. 

3. THE SHROUD WOULD SEE TEMPERATURES OF 400°F FOR HOUR PERIODS. 

4. SHELL ACCELERATIONS FROM MARTIN'S SECOND LOAD CYCLE WOULD BE USED TO 

DETERMINE LOAD FACTORS. 

5. THE 45. P ACROSS THE SHROUD WALL WOULD BE 0.1 PSI OR LESS. 

6. THE DRIVE MECHANISM WOULD BE A REDUNDANT DRIVE WITH A MOTOR AND GEAR BOX 

DIRECTLY CONNECTED TO EACH SIDE OF THE SHROUD. 

7. THE WORST CASE ON-ORBIT LOADS ARE FOR THE CONDITION OF A MOTOR FAILURE 

WITH THE SHROUD THEN BEING DRIVEN FROM ONE SIDE ONLY. 

THE CONCEPT STUDIED IS AS FOLLOWS: 

FOR THE ENVIRONMENT CONSIDERED, A SHROUD WEIGHT OF 14 LBS. IS FEASIBLE. 

"lfe-REL.SPRIAL HANDLIt4iG 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 -Ttni---cruarkcyNsHANDLING 

ATS ALIGNMENT STUDIES 

AREAS STUDIED: 

1. MECHANICAL JOINT SLIPPAGE 

2. SHELL PRESSURIZATION 

3. 1G LOAD RELIEF 

4. VEHICLE THERMAL DISTORTIONS 

DISCUSSION: 

1. MECHANICAL JOINT SLIPPAGE 

o WORST CASE CONSIDERED: WORST TOLERANCE STACK-UP, 

SINGLE FASTENER JOINTS, MOVEMENT IN WORST DIRECTION. 

o RESULTS: ANGULAR MIS-ALIGNMENT OF THE LINE OF SIGHT BETWEEN 

THE EYE-PIECE AND THE SCANNER MIRROR IS 8.52 ARC MIN. 

2. SHELL PRESSURIZATION 

o 0 G P CONSIDERED AT INITIAL ALIGNMENT, 5 PSI + 0.2 PSI 

AP CONSIDERED ON-ORBIT. 

o RESULTS: ANGULAR MIS-ALIGNMENT OF THE LINE OF SIGHT BETWEEN 

THE SCANNER MIRROR AND THE FIXED-FOLD MIRROR IS 2.35 ARC MIN. 

FOR A AP OF 5 PSI FOR A AP OF 4.8, THE MIS-ALIGNMENT IS 

2.26 ARC MIN. AND FOR A AP OF 5.2, IT IS 2.45 ARC MIN. 

228 

ifireilg SPECIAL HANDUNG 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

ATS STRUCTURAL ANALYSIS 

ATS ALIGNMENT STUDIES 

(CONT'D) 

DISCUSSION - (CONT'D) 

3. 1G CONDITION RELIEF 

o RELEASE OF DEFLECTION OF COMPONENTS IMPARTED BECAUSE 

OF 1G FIELD DURING VEHICLE INSTALLATION. 

o RESULTS: ANGULAR MIS-ALIGNMENT OF THE LINE OF SIGHT 

BETWEEN THE EYE-PIECE AND THE OBJECTIVE IS 2.65 ARC SEC. 

4. VEHICLE THERMAL DISTORTIONS 

o NOT SIGNIFICANT DUE TO RADIATOR 

229 

SPEC! t, HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 *--M-141-- SPECIAL HANDLING 

ATS STRUCTURAL ANALYSIS 

FUTURE WORK PLANNED 

1. UPDATED STRUCTURAL ANALYSIS OF TELESCOPE, SCANNER AND SHROUD 

o LATEST CONFIGURATION 

o LATEST LOADS 

o THERMAL EFFECTS 

o SHELL PRESSURIZATION EFFECTS 

2. ADDITIONAL WEIGHT ORIENTED STRUCTURAL OPTIMIZATION STUDIES TO 

CONTROL SYSTEM WEIGHT EFFECTIVELY. 

3. STRUCTURAL ANALYSIS OF EXTERNAL FIXED-FOLD MIRROR. 

4. DETERMINATION OF SHELL FLEXIBILITIES WHEN SHELL IS PRESSURIZED 

TO 5 PSI. 

5. UPDATED ALIGNMENT INFORMATION TO REFLECT LATEST STRUCTURAL CONFIGURATIONS 

AND ALSO LATEST SHELL FLEXIBILITY INFORMATION. 

230 

SPECIAL HANDLING 
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RELEASE 1 JULY 2015 Ra. SPECIAL HANDLING 

ATS DESIGN LOADS 

THE ATS DESIGN LOAD FACTORS WERE DERIVED FROM THE BIRDCAGE DESIGN 

LOADS. THE BIRDCAGE DESIGN LOADS ARE AS FOLLOWS: 

LIMIT LOADS (ULT. = 1.4 x LIMIT) 

LOAD CONDITION Nx (G's) Ny (G's) Nz (G's) 

MAX. X CONDITION 

MAX. Y CONDITION 

MAX Z CONDITION 

+ 7.0 + 0.5 

+ 2.1 + 1.25 

- 0.67 

+ 2.1 

- 0.67 

+ 0.5 

+ 0.5 

+ 0.5 + 1.25 

REF: MINUTES OF BIRDCAGE TM ON LOADS AND STRUCTURAL COMPATIBILITY (3/28/67) 

TO ACCOUNT FOR AMPLIFICATION OF THE LOADS, THE MAX. X CONDITION WAS 

INCREASED TO + 10G's. THE REMAINING LOAD FACTORS WERE THEN INCREASED 

BY THE RATIO OF 10/7. THE DESIGN LOADS ARE THE FOLLOWING: 

LIMIT LOADS (ULT. = 1.4 x LIMIT) 

LOAD CONDITION Nx (G's) Ny (G's) Nz (G's) 

MAX. X CONDITION 

MAX. Y CONDITION 

MAX Z CONDITION 

+ 10.0 + 0.72 + 0.72 

+ 3.0 + 1.8 + 0.72 

- 1.0 

+ 300 + 0.72 + 1.8 

- 1.0 

231 

.--'1ERE,L. SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 ISUL SPECIAL HANDLING 

PROTECTIVE SHROUD DESIGN LOADS 

THE PROTECTIVE SHROUD LIES BETWEEN STATIONS 518 AND 566. THE MAXIMUM 

LOAD FACTOR FOR A POINT BETWEEN THESE STATIONS WILL BE USED. 

REF: SHELL ACCELERATIONS FROM THE MARTIN COMPANY 2ND LOAD CYCLE 

DATED NOVEMBER 14, 1966. 

LOAD CONDITION 

LIMIT LOADS (ULT. = 1.4 x LIMIT) 

AXIAL G's YAW G's PITCH G's 

LAUNCH 

STAGE 0 THRUST 

TERMINATION 

STAGE I 

SHUTDOWN 

STAGE II 

IGNITION 

+ 2.8 

+ 0.59 

+ 3.6 

- 1.8 

+ 4.1 

- 1.3 

+ 5.6 

-2.7 

+ 0.41 

- 0.24 

+0.05 

+ 0.42 

- 0.41 

NEGLIGIBLE 

+ 0.80 

- 0.44 

+0.05 

NEGLIGIBLE 

NEGLIGIBLE 

THE CONDITIONS CHOSEN WERE MAX. LATERAL G's (LAUNCH) AND MAX. AXIAL G's 

(STAGE II IGNITION). THESE CONDITIONS ARE SHOWN ON PG. 2-320 OF THE EAR. 

THEY ARE USED CONSISTENTLY THROUGH THE ANALYSIS OF THE PROTECTIVE SHROUD. 

232 

SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 'SEMI SPECIAL HANDLING 

ATS WEIGHT STATUS 

CURRENT ESTIMATE 

TELESCOPE 149.22 LB. (74.61 LB.) 

EXTERNAL FIXED-FOLD MIRROR 29.50 LB. (14.75 LB.) 

PRESSURE WINDOW 8.42 LB. ( 4.21 LB.) 

SCANNER 111.60 LB. (55.8 LB.) 

PROTECTIVE SHROUD 43.72 LB. (21.86 LB.) 

SUN-SENSOR 1.50 LB. ( 0.75 LB.) 

TOTAL 343.96 LB. (171.98 LB.) 

233 

SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 --IBM- SPECIAL HANDLING 

DETAILED BREAKDOWN 

TELESCOPE 

OBJECTIVE END 25.99 

LOW POWER GROUP 20.79 

SHEAT MOUNT 1.00 

TRANSITION ASSEMBLY 6.88 

PECHAN ASSEMBLY 6.20 

ZOOM ASSEMBLY 5.20 

EYE-PIECE ASSEMBLY 2.80 

ELECTRICAL 5.75 

74.61 LB. or 149.22 LB/VEHICLE 

EXTERNAL FIXED-FOLD MIRROR 

MIRROR 11.00 

BEZEL 2.10 

POTTING 0.87 

FITTINGS 0.78 

14.75 LB. or 29.5 LB./VEHICLE 

PRESSURE WINDOW 

GLASS 4.21 

4.21 LB. or 8.42 LB/VEHICLE 

234 

----Ife-R-EL,SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

DETAILED BREAKDOWN 

TRACKING PEDESTAL 

PEDESTAL AND HOUSING 6.35 

YOKE 2.28 

MIRROR 11.14 

BEZEL 3.15 

POTTING 0.88 

HARNESS AND CONNECTORS 6.00 

MOTORS, ENCODERS, ETC. 26.00 

55.80 LB. or 111.60 LB./VEHICLE 

PROTECTIVE SHROUD 

STRUCTURE 11.95 

DRIVE 5.86 

INSULATION 2.30 

PAINT AND COATINGS 1.00 

DISCONNECTS AND LAUNCH LOCKS 0.75 

21.86 LB. or 43.72 LB./VEHICLE 

SUN SENSOR 

SUN SENSOR 0.75 

0.75 LB. or 1.50 LB./VEHICLE 

SPECIAL HANDLING 5 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 -11-0141-- SPECIAL HANDLING 

STRUCTURAL DYNAMIC ANALYSIS 

A. THREE COMPONENT DYNAMIC MODELS 

TELESCOPE 

a. NUMBER OF D.O.F. = 126 

b. ALL OPTICAL ELEMENTS MONITORED (12 ELEMENTS) 

c. BOUNDARY CONDITION = FREE-FREE 

d. TWO ATTACH POINTS TOTALING NINE (9) D.O.F. 

e. SIX (6) RIGID BODY MODES 

FIXED-FOLD 

a. NUMBER OF D.O.F. = 14 

b. BOUNDARY CONDITION = FREE-FREE 

c. THREE (3) ATTACH POINTS TOTALING NINE (9) D.O.F. 

d. SIX (6) RIGID BODY MODES 

SCANNER 

a. NUMBER OF D.O.F. = 40 

b. BOUNDARY CONDITION = FREE-FREE 

c. THREE (3) ATTACH POINTS TOTALING EIGHTEEN (18) D.O.F. 

d. EIGHT (8) RIGID BODY MODES 

236 

'HMI_ SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 ----I-MEL SPECIAL HANDLING 

STRUCTURAL DYNAMIC ANALYSIS - (coned) 

B. SUBSYSTEM MODEL 

1. THREE (3) COMPONENT MODELS COUPLED THROUGH SHELL STIFFNESS 

MATRIX. 

2. TOTAL D.O.F. = 180 

3. MODE SHAPES AND FREQUENCIES WILL BE COMPUTED. 

C. COUPLING STIFFNESS MATRIX 

PRESSURIZED, NON-PRESSURIZED. 

D. OBJECTIVES OF DYNAMIC ANALYSIS 

1. EVALUATE DESIGN BY ANALYSIS OF MODE SHAPES 

(STRUCTURAL INTEGRITY AND OPTICAL PERFORMANCE) 

2. EVALUATE EFFECTS OF INTERNAL DISTRUBANCES ON SUBSYSTEM PERFORMANCE. 

3. EVALUATE STRUCTURE - CONTROLS STABILITY. 

4. EVALUATE EFFECTS OF EXTERNAL DISTRUBANCES ON SUBSYSTEM PERFORMANCE. 

5. EVALUATE EFFECTS OF INTERNAL DISTURBANCES ON D SYSTEM. 

E. PRESENT STATUS 

1. TELESCOPE MODEL IS DEFINED AND MASS AND STIFFNESS PROPERTIES CALCULATED. 

EIGENVALUE RUN IS IMMINENT. (MODE SHAPES AND FREQUENCIES - MARCH 15) 

2. SCANNER MODEL IS DEFINED. (MODE SHAPES AND FREQUENCIES - MARCH 22) 

3. FIXED-FOLD MODEL IS DEFINED. (MODE SHAPES AND FREQUENCIES - MARCH 22) 

237 

SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 --SENET-- SPECIAL HANDLING 

SUBSYSTEM ALPHA TELESCOPE 

126 DEGREES OF FREEDOM 

0 

SHELL ATTACH POINT C) 

1. ELEMENTS 1 & 2 

2. OBJECTIVE TUBE 

3. OBJECTIVE INTERMEDIATE FITTINGS 

4. LOW POWER DRIVE MECHANISM 

5. FIRST LOW POWER GROUP 

6. INTERMEDIATE TUBE 

7. APERATTEtE STOP 

8. INTERMEDIATE ELBOW FITTING 

9. SECOND LOW POWER GROUP 

10. FOLD MIRROR 

11. ELBOW MECHANISM 

12. PRISM DRIVE MECHANISM 

13. PECHAN MECHANISM ED 14. ELEMENT #9 

15. ELEMENTS #10 thru 13 

16. ELEMENTS #14 and 15 

17. ELEMENTS #16 and 17 

18. ZOOM DRIVE MECHANISM 

19. ELEMENTS #18 and 19 

20. ELEMENT #21, FILTER 

21. EYEPIECE 

0 

SHELL ATTACH POINT 

11••"- 

238 

SPI HANDLINm 
cl.CC.V. ft) & 

ir‘ 

Qopdx.ovtky Ag 

/e3 

Y 

4. 

410 ° r-eeclOry-% 

SPECIAL HANDLING NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SCANNER DYNAMIC MODEL 

---Ifig-T Q --SPitIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

FIXED-FOLD DYNAMIC MODEL 

• 

• 

240 

7SteR{4- SPECIAL: HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 ---SEGRET- SPECIAL HANDLING 

g. HISTORY 

1. SUBCONTRACTOR FOR ALPHA SUBSYSTEM EXPRESSES NEED FOR SHELL 

FLEXIBILITY INFORMATION. THE INFORMATION IS NEEDED FOR 

DESIGN PURPOSES (MIS-ALIGNMENT STUDIES, COMPONENT DYNAMIC 

ANALYSIS, ETC.). 

2. ASSOCIATE CONTRACTOR SUBMITS SHELL DEFLECTION INFORMATION. 

THIS INFORMATION DOES NOT FILL NEEDS (GIVES NO INDICATION 

OF SHELL FLEXIBILITIES). 

3. ADDITIONAL INFORMATION REQUESTED FROM ASSOCIATE. ASSOCIATE 

STATES THAT REQUIRED SHELL FLEXIBILITY INFORMATION WOULD NOT 

BE AVAILABLE PRIOR TO JUNE 30, 1968. 

4. DECISION IS MADE THAT GE WILL PERFORM COMPLETE SYSTEM DYNAMIC 

ANALYSIS USING COMPONENT MODELS GENERATED BY SUBCONTRACTOR 

AND USING THE PRESSURE SHELL TO TIE THE COMPONENTS TOGETHER. 

5. IN ORDER TO PERFORM THE DYNAMIC ANALYSIS AND TO SUPPLY THE 

SUBCONTRACTOR WITH THE INFORMATION HE NEEDS, IT IS DECIDED 

THAT GE WILL, USING ASSOCIATE DRAWINGS, DEVELOP A FLEXIBILITY 

AND STIFFNESS MATRIX REPRESENTING THE SYSTEM MOUNTING POINTS. 

SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 ISIRET- SPECIAL HANDLING 

PROCEDURE USED TO OBTAIN STIFFNESS MATRIX 

1. MODEL PRESSURE SHELL STRUCTURE USING DAC DRAWING# 1B72094 

o DETERMINE MODEL CONFIGURATION 

o DETERMINE SECTION PROPERTIES 

o SET-UP BOUNDARY CONDITIONS. 

2. APPLY UNIT FORCES AND MOMENTS AT SYSTEM MOUNTING POINTS 

TO OBTAIN DEFLECTIONS AND ROTATIONS AT EACH MOUNTING POINT. 

THE FORCES AND MOMENTS ARE APPLIED IN THE RADIAL, TANGENTIAL 

AND LONGITUDINAL DIRECTIONS TO OBTAIN 6 DEGREES OF FREEDOM 

FOR EACH POINT. THE "MASS" (MECHANICAL ANALYSIS OF SPACE 

STRUCTURES) PROGRAM WAS USED TO OBTAIN THE DEFLECTIONS AND 

ROTATIONS. THE PROGRAM UTILIZES THE GE 635 COMPUTER SYSTEM. 

3. THE OUTPUT INFORMATION IS IN THE X, Y, Z COORDINATE SYSTEM. 

THE OUTPUT IS THEN TRANSFORMED INTO THE RADIAL, TANGENTIAL 

AND LONGITUDINAL COORDINATE SYSTEM USING A PROGRAM WRITTEN 

FOR THIS PURPOSE USING THE GE 605 COMPUTER SYSTEM. 

4. ASSEMBLE THE TRANSFORMED OUTPUT DATA INTO A 36 x 36 INFLUENCE 

COEFFICIENT MATRIX (REPRESENTS 6 DEGREES OF FREEDOM AT 6 MOUNTING 

POINTS). . 

5. INVERT THE INFLUENCE COEFFICIENT MATRIX TO OBTAIN A STIFFNESS 

MATRIX. 

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FUTURE ANALYSIS REQUIRED 

1. SHELL FLEXIBILITIES WHEN SHELL IS PRESSURIZED TO ON-ORBIT 

PRESSURE OF 5 PSI. 

o INFORMATION NEEDED FOR DYNAMIC ANALYSIS AND 

ALIGNMENT STUDIES. 

2. UPDATING SHELL FLEXIBILITIES TO REFLECT CHANGES TO DACO 

SHELL. 

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Eye Hazard 

Airforce Questions pertained to: 

a) The ability of the sun shutter to protect against enemy lasers 

b) The ability of the sun shutter to protect against specular solar 

reflections 

c) Whether GE considered the transmission characteristics of lens 

coatings in the eye hazard calculations h 

GE Comments in reply: 

a) The sun shutter will require approximately 50 to 100 milli-seconds 

to close. This response is approximately the same as the blinking 

response of the eye and is not believed to provide significant 

additional protection against lasers and specular reflections 

b) GE did not consider the coating properties in the eye hazard 

analysis,and will accept an action item to do so. 

SPielAL HANDLING 
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LEAR SIEGLER ACTION ITEMS FROM PDR 

I Optical 

1. How is cleanliness maintained and what is requirement on Kollmorgen? 

Compoucnts cleaned to and assembled in, Class 100; afterwards 

maintained in Class 10,000. Vents small,.staggered and fitted 

with microgrove filters. 

2. Optical error analyis and error budget incl. mech. interface 

Eckert has analysis. Worst case, misalignment adds up to 

6.2 ,nuns. of ale (spread o,e = 0.9 mil = 1 depth of focus 

distance which = 1 mil) = (or projection lens MTF to he reduced 

to 72% of ali.g..ed con!iition). 

3 Optical Prescription - Dr. Eckert 

4. Data from Chicago Miniatore on lama life for OFF-ON vs. constant 

applied power No significant life difference. Low input may 

be better for shock and vibration. Permeation is a function of 

temperature ,;(, constant pone: TAptit might make helium permeation 

Worse. 

5 Revise Visual Display Proiector such that the image is not transmitted 

through the film base. 

1) Invert film 

2) Keep module the same !:-.,t cha.igP directicrn of ihroil it. 

1) if is i.nverrrld, scratches would then b^ likely to 

occur on emulsion side of the filr which will definitely 

destroy 71'ormauioa. 

Scratees c the has,?. Lay rJw iostroy information due 

to depth of focus. 

2) If the modulo: remaius th- sa-=, the proi=ctor will have to he 

rPdesigaed such that the light will pass through tie prism 

tuea the has= and the the erulsioa This redesign is 

considerable and may rc:ilAt ;r1 larger prolection. This is 

under proposed investigation - plane are propeseo tJ“t 

fendei. 

268 

--SfaIEL. SPECIAL H NDLING 
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II Mechanical 

1) Furnish GE with stress analysis of the VDP and film module 

documenting the design accelerations used. 

This action item was not answered to the satisfaction of GE. 

However, due to relocation of the Visual Display Projector to 

the "D" panel and the subsequent change in mounting, the 

analysis to date no longer applies. 

2) Feasibility of making lamp slides interchangeable 

They are now interchangeable. 

3) What is weight reduction by going to Beryllium. 

The weight saving for each Visual Display Projector by going 

to Beryllium is 2.1 lb. excluding film module. 

The weight saving for each film module is 0.33 lbs. 

The total weight saving per vehicle is 9.8 lbs. 

4) What is the maximum temperature that the component will see in the 

standby mode in the event of possible coolant loss? 

In the sLandby mode there is lesr tLan 30 milliwatts power 

dissipation which will cause a negligible temperature rise. 

If operated continuously at a screen brightness level of 

15 foot lamberts with the existing lamp design the lamp power 

dissipation will be 6.5 watts and that of the 'fiower supply, 

brightness control, solenoid and arithmetic unit will be 14.2 

watts. Of this power, 6.5 watts will be conducted directly to 

the heat sink. 

The assumptions made are that the front plate is bolted to the 

console at four points through projecting g ears, the temperature 

of the supporting structure is 80 F, the front surface of the 

VDP is radiating to 80uF and the remaining five surfaces are 

radiating to 110° F. Cabin pressure is 5 psis and no convection 

cooling can take place. 

269 

"SteR-EL SPECIAL HANDLING 
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The temperature of the lamp envelope was found to stabilize 

at 290° F. The maximum circuit board temperature was found to 

be 193° F. Both of these temperatures are permissible but 

stressing of the electronic components will be a little 

greater than normal. 

5) Drag brake design instead of motor shunt - no funds. 

6) Insure torquer lockout during module insertion and removal. 

A limit switch was added which is operated by the module 

locking bolt. 

7) Substitute weight breakdown. 

This was answered to GE's satisfaction. 

III Electrical 

1) Lear Siegler will supply schematics to GE. This has been completed. 

to GE's satisfaction. 

2) Supply EMC Plan. 

The document has been received by GE and is being reviewed. 

3) Voltage/motor size trade off study - no funds. 

4) Electronic simplification for aperture contrast ratio 10:1 - no 

funds. 

General 

1) GE define maximum depressurization rate. 

From 19.0 psiA to 5 + .2 psiA. at a rate equal to or less 

than .5 psi/sec. 

2) Latest information on "gloved hand" - OPEN. 

270 

--I-EMI. SPECIAL HANDLING 
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RELEASE 1 JULY 2015 SPECIAL HANDLING 

Thermal data for worst case. 

This information was sent to Lear Siegler upon which was based 

their reply to Mechanical Item # 4 above. 

4) Revise specification to include proof pressure, leakage, 

cleanliness of coolant parts. 

Pressure requirements were added to specification. 

Leakage and cleanliness awaiting answers from systems needs 

interface with DAC. 

5) Maximum/minimum coolant temperature 

Maximum temp. - 115° F - VDP non-operating 

30 min. max. 

100° F - VDP operating 

Minimum temp. - 60° F 

6) Film module specification is being circulated for signatures. 

7) Design constraints for module handle - OPEN 

This is related to gloved hand requirement. Concept has been 

arrived at, at Lear Siegler. 

8) Direction on module identification. 

Space for label is being included on side opposite magnetic 

material and also on end containing the handle, such the-the module 

can be identified whether it is in the rack or on the magnetic 

latch on the console. 

9) Direction on need for wrong module indication. 

It is needed. 

10) Define electrical interface completely. 

The missing item was rise time. A 1 microsec. rise time requirement 

was added to specification. 

S? AL HANDL NG 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 -ISIZEL. SPECIAL HANDLING 

11) Revise specification to include octal numbering. This 

has been done. (Estimated weight saving 0.15 lb.) 

12) Define range of Alpha numeric brightness. Brightness range 

defined as 0 to 10,000 ft. lamberts. Brightness as viewed by customer 

at Lear Siegler was approximately 8000 ft. lamberts. 

-Ife14-g- SPECIAL I-IANDUNG 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

ANSWERS TO P.D.R. QUESTIONS 

Question 63 - Statistical analysis of focus adjustment requirements. 

We have not furmulatnd a statistical approach h6t have devoted considerable effort 

toward defining the problem. 

Some factors are: 

1) Module Material 

2) Type of film data 

3) Temperatk,re environment 

4) Mechanical Intertaces 

S) Method used tcs determine resolutions 

Human factors preblem - when is scene in Locus - wLat 

.)o focus . 

W° have a plan tr start Lear Siegler workini, coward L,.t. solutions of some of these 

problems. 

1) Modify test fixture fcr 

a) Module io,;erticr, 

Proecticn lamp 

c) External electrooics 

d) Power 

e) Logic 

2) Fabricate 1 or 2 film modeles including thu ■ oilowing: 

a) Berylium 

FilT Clamping 

c) Filr: plaqn 

d) Drag brake 

e) Handle 

Loc:Ang Device 

273 

---1-EG-M. SPECIAL HANDLING 
SPECIAL HANDLING 

2 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3) Prepare two film setups to measure wearscratching,and effect 

of projecting image througi the Lase. " 

a) With emulsion side away from rollers 

Witk em.ilsion side on rollers. 

Each will have binary descriptor's, consistent with the 

present brassboard, and also special wear auo resolution targets. 

i . Qu,2stiou t c - Desirability t4 udex marks on focus knob for pre-adjustment. 

This is related to question and is related to :.he necessity for -

focussing. The drive mechanism has the mechanical stability: 

1) Piuued phosphor bronze drive. 

2) Teflou plugs 0.1 proj,, rtir,n lens barrel thread. 

inch diameter k,lo;). 

4) 4.1 drive ratio 

5) 45° of knob gives .001 inch travel of lens. (full depth of focus). 

QuesLion 65 Use of Beryllium. in film module. 

1) We saving r mod,Ile 0.33 lb. 

2) Weight saY;na per vehicle 5.25 lb. 

3) Lower t-mpe,-aturr.- ccefficieat. 

4) Better niiiiensio,lal stabilit. 

5) Closer tolerance 

6) Better tit 

7) Reduced teuus proble-:1 

8) Hi.her (app -.N. 4X) 

Inft „ ig....SPEOIAL HANDING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

' -"SICRE-L, SPECIAL HANDLING 

3. 

Question 14 - Retrieval Time 

Provided there are at least three consecutive numbered frames preceding 

the commanded frame, the retrieval time is as shown .35 + N/100 seconds 

recPipt of command. 

tfeREL SPEc141. HANDLING 
~`EN1-E-T_ SPECIAL HANDLING NRO APPROVED FOR 

RELEASE 1 JULY 2015 

VDP OPTICAL ANALYSIS 

I REQUIREMENTS 

MAGNIFICATION 

V' FILM"-, 6.5" DIAMETER SCREEN 

M-13 

RE SOLUTION 

ON AXIS 228 LP/MM ON FILM 

AT 6 : 1 CONTRAST 

0.9 Rs 204.5 LP /MM ON FILM 

AT 6 : 1 CONTRAST 

276 

• T HANnLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

A 

II SYSTEM 

LIGHT I FILM ' PROJECTION SCREEN 1 

SOURCE' BLOCK LENS 

PROJECTION LENS 

COOKE TRIPLET 8 PARAMETERS 

CAN ADJUST 7 SEIDEL ABERRATIONS 

PLUS MAINTAIN DESIRED FOCAL LENGTH 

CHOICE OF f# = FOCAL LENGTH 

DIA. OF ENT. PUPIL 

= 3.5 

THIS CORRESPONDS TO CUT OFF FREQUENCY OF 520 LP/MM 

2 x 228 

, = 0.55 

SCREEN - REAR PROJECTION - HIGH 

FREQUENCY CUT OFF DUE TO GRAIN SIZE 

277 

SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 italig- SPECIAL HANDLING 

III OPTICAL ANALYSIS 

DESIGN 

Screen 

i l l 

Film Cooke 

Block Triplet 

Film 

COMPUTATION 

RAY TRACING - DETERMINE REFRACTION AT EACH SURFACE 

- FROM POINT SOURCE TRACE MANY RAYS (UP TO 750 POSSIBLE 

BUT 75 USED IN THIS CASE). RAYS ARE UNIFORMLY DISTRIBUTED OVER SURFACE OF ENTRANCE PUPIL. 

- THE DISTRIBUTION OF RAY INTERSECTIONS IN IMAGE PLANE 

YIELDS SPOT DIAGRAM. 

eRg- SPEC AL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

- FOURIER TRANSFORMATION OF SPOT DIAGRAM YIELDS MTF WHICH 

IS GEOMETRIC MTF 

TO INCLUDE DIFFRACTION MULTIPLY BY MTF OF AN ABERRATION 

FREE DIFFRACTION LIMITED SYSTEM OF THE SAME N.A. 

279 

. SITGREI SPECIAL HANDLING 
NRO 

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NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

CONCLUSIONS 

I A X10 MAGNIFIER WILL BE REQUIRED TO MEET THE 228 LP/MM 

RESOLUTION SPECIFICATION. 

II OUR STATISTICAL ANALYSIS USING THE LSI ASSIGNED SPACING 

AND CURVATURE TOLERANCES AGREES WITH THE LSI DETERMINED 

NOMINAL PERFORMANCE PREDICTION. 

III PRELIMINARY ANALYSIS OF THE ANGULAR TOLERANCES OF THE 

PRISM, MIRROR, AND SCREEN ARE CONSISTENT WITH THE 

DETERMINED DEPTH OF FOCUS. 

IV DECENTERING AND TILTING OF ALL SURFACES MUST YET BE 

INVESTIGATED. 

V ANALYSIS OF THE CONDENSER SYSTEM MUST YET BE PERFORMED. 

ifelia. SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 -1EGREI... SPECIAL HANDLING 

DRIVE K ELECTRONICS 

MARCH PDR 

DESIGN FEATURES 

o PROVIDES BOTH A PRIMARY AND A HOOK-UP CONFIGURATION IN 

THE EVENT OF A GYRO FAILURE. 

o PROVIDES DIGITAL INTEGRATOR TO COMPUTE POSITION COMMANDS 

AND DIGITAL SUBTRACTOR TO ESTABLISH POSITION ERROR SIGNAL 

(APPROX. 175 IC'S). 

o PROVIDES CIRCUIT ISOLATION OF CRITICAL AND NON-CRITICAL 

CIRCUIT FUNCTIONS. 

o "BORROWED" CIRCUIT TECHNIQUES/ CIRCUITS FROM DRIVE A 

ELECTRONICS. 

o MODULAR CONSTRUCTION WITH INDIVIDUAL CIRCUIT FUNCTIONS ON 

SEPARATE REMOVABLE PANELS. 

o CAREFUL ATTENTION TO NOISE PERFORMANCE (CIRCUIT DESIGN, 

SHIELDING, P.S. FILTERING). 

DESIGN STATUS 

o PRELIMINARY COMPONENT SPEC WRITTEN. 

o BREADBOARD OF MAIN DRIVE ELECTRONICS BUILD AND UNDERGOING 

FINAL FUNCTIONAL TESTS PRIOR TO INCORPORATION INTO BRASSBOARD. 

1:. 'fi:A4\W* 

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fl 

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• 
NRO APPROVED FOR SHEET RSV 

RELEASE 1 JULY 2015 i-EREL sPEcitil MilpLING 

REVISIONS 

LIR DtSCRIPTION DATE I APPROVED 

I. SCOPE 

1.1 Scope 

This drawing covers the detail requirements for silicon, junction, N-channel field 

effect transistors selected for use in missile and space vehicle applications. The 

closest equivalent transistors are: 

SUFFIX NUMBER TYPE NUMBER 

P1 2N4445 

P2 2N4446 

P3 2N4447 

P4 2N4448 

SPECIFICATION CONTROL DRAWING - NO CHANGE SHALL BE MADE TO THE DESIGN, CONFIGURATION, 

MATERIAL, PARTS OR MANUFACTURING PROCESS, WITHOUT PRIOR WRITTEN APPROVAL OF MOL 

DEPARTMENT, PARTS AND APPLICATIONS ENGINEERING, 

UNLESS OTHERWISE SPECIFIED SIGNATURES DAY 

DIMENSIONS ARE IN INCHES. 

TOLERANCES ON: 3[.1 DRAWMy 

C 44047". c...4 3 

saZi 

GENERALSELECTRIC 

MOL DEPT LOC Phila., Pa. 

MO YR 

3 G7 

1' 3 

GR 

'7 

FN 90,1•F (11-65) RRINTED IN U.S.A. 

TRANSISTOR, SILICON, JUNCTION, 

N-CHANNEL, FIELD EFFECT 

FRACTIONS DECIMALS ANGLES 

ALL SURFACES V 

MATL— MFG 

MATLS 

ra 3 

CODE IDENT NO. 

23991 R11009 

SIZE 

A 

SCALE 'SHEET 1 OF 12 

AL HANDLING 
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Tian 

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• 

EL F.0 o s 

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fil.rzi; pinP Li RE-le 1 ai4PL / 1744 a 

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ctronicsPackage 

NRO APPROVED FOR 

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SECRET SPECIAL HANDLING 

294 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SECRET SPECIAL HANDLING 

WEIGHT - SIZE - POWER 

SIZE WEIGHT 

INPUT 

POWER 

MAIN DRIVE K 

ELECTRONICS 8"x9"x12.5" 20.5 lbs. Peak 141w@ 24v 

(KO-K2) 

Stby 50w@ 24v 

INTERNAL MECHANISMS 

ELECTRONICS 8"x9"x6.5" 16.5 lbs. Peak 8614@ 24v 

(K3-K7) Stby 8/4@ 24v 

TOTAL 8"x9"x19" 37 lbs Peak 22714@ 2417 

Stby 58w@ 2417 

SECR T SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 -ffeitEr SPECIAL HANDLING 

POWER BREAKDOWN @ 2417 

o MAIN DRIVE K ELECTRONICS (KO-K2 

DISSIPATED DELIVERED INPUT 

KO 9.5 (9.5 0 9.5 (9.5) 

K

1 7.2 (4.0) 8 (0) 15.2 (4) 

K2 26.6 (10.5) 58 (5.3) 84.6 (15.8) 

K10a 20 (5) 12 32 (5) 

TOTAL 141.3 (35) @ 2417 

o INTERNAL MECHANISMS ELECTRONICS (K3-K7) 

DISSIPATED DELIVERED INPUT 

K3 3.4 (1.2) 5.5 8.9 (1.2) 

K

4 2.8 ( .6) 5.5 8.3 ( .6) 

K

5 

2.7 ( .6) 24.3 27.0 ( .6) 

K6 1.6 ( .6) 12.1 13.7 ( .6) 

K7 2.2 ( .6) 20.8 23.0 ( .6) 

K

10b 4.0 (4) 1.0 5.0 (4) 

TOTAL ......... . . 85.9 (8) @ 24v 

--St-Mr SPECIAL HANDLING 

296 
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ntructur,.:. 

' attand pages contain a weight aummary. of the 39 lb. flat caci: 

Ft.r.o.t.ture esc!sl.:in, the 45 lb: flat pack alamin.an n:.:ructure desif4a and 

aTIcInf4 thc diffor:mIce in weight of the electrenj.c Loxes Al throng A19 

t(, nodular deni%n. 

!tail calculations substantiating the weights aro also attached: 

l/RIrE "4" WICKS (SIPIMATIY) • - FLAT PACK MODULAr• PLAT PACK 

• .At BOXF'S IA r; RoxFs MAO BOXES 

i • :.7 A16 3.17 2.93 2.93 

rOUTR A19 8.03 751 . 7.51 

• 2 Al8 3.04 .2-71 2.71 

i

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oubtotal A.1_ Lo A19 31.71 28.02 .... 2 2.49.1 t 

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2.03 . , 1.79 1.79 

.. 

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5,8 A14 1.87 1.63 1,63 

4 ?..6 ' A15 1.76 1.44 1.44 1 

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316 
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319 

Ile-REL SPECIAL HANDLING 
PANEL CONTROLS & DISPLAYS 

SCANNER STOW (R.P) 

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320 
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RELEASE 1 JULY 2015 SPECIAL HANDLING 

LEFT HAND (MAGNIFICATION) CONTROLLER FUNCTIONS 

CONTROL MAIN OPTICS GAIN 

• CONTROL ATS GAIN/ZOOM 

• GENERATE TARGET VOTES 

• GENERATE CUE HOLD COMMAND 

• SWITCH MCS FROM ATS TO MAIN OPTICS 

• RELEASE ATS HOLD COMMAND 

321 

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:1!..151.1.111•11E1111••1111131 MMINV.60s......- 

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LEFT ELM WAGNIFICATICA CCT2CLLE1, 

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323 

-IBM-- SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 -T, SPECIAL HANDLING L.

DRIVE K GYRO REQUIREMENTS 

• CONCEPT: Gas Bearing floated gyro with support electronics, Rate Mode 

. SIZE: 85 cubic inches (Gyro plus Electronics Package) 

. WEIGHT: 5.1 pounds less Cable 

• POWER: 5 watts electronics plus Heater Power 

• NOISE: PSD Envelope and RMS Requirement 

• FREQUENCY RESPONSE: Third Order with breaks specified 

• THERMAL ENVIRONMENT: 0 to 100 degrees F Vacuum Space 

• MONITOR FUNCTIONS: 4 TLM Discretes -Overheat 

-Control Heat 

-Saturation 

-Wheel Sync 

• MAXIMUM COMMONALITY with Drive A gyro 

plus Test Points 

324 
SPIN MOTOR 

SUPPLY 

EXCI T . 

SG 

TIMING & 

CONTROL 

T2 

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325 

COMMAND 

TCA HEATER 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 IMEL SPECIAL HANDLING 

RATE GYRO ASSEMBLY 

4,5 V 

22 - 31 VDC SWITCHING POWER ± 12 V 

PRE-REG SUPPLIES + 25 V 

-1ErrEL SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

COMMONALITY STUDIES 

I. Gyro PSD envelope and Transfer function specified as a sub-system requirement: 

A. PSD Envelope can be met by a Gyro similar to Drive A Gyro. 

(01ITS )2 

Rad/Sec 

2,.X 1C) 

10 3 

3rN1C 3 

4_--ph. Rad/Sec 

4' Sacs 2000 

B. Transfer Function 

E (s) = K a = .01 sec (caging loop) 

(s) (as + 1)(bs + 1)(cs + 1) 

b = .0009 sec (gyro) 

c = .0002 sec Max (Electronics) 

1. Time constants a & c are functions of electronics and adjustable. 

2. Time constant b is J/CD and only CD is conveniently adjustable. 

It is a function of fluid viscosity and damping gap. 

3. CD required to be 2.5 x 105 at 160 degrees F versus 5 x 104 at 

130 degrees F for Drive A. 

4. Maximum commonality by using same gyro as Drive A with different 

fluid. 

326 
--'11-OR-EL SPECIAL HANDLING NRO APPROVED FOR 

RELEASE 1 JULY 2015 

ALPHA SUBSYSTEM 

o RELIABILITY ANALYSIS 

o SAFETY ANALYSIS 

o MAINTAINABILITY ANALYSIS 

327 

------Stef-E-T, SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 --'--SnitET--SPECIAL HANDLING 

ATS RELIABILITY DESIGN CRITERIA 

• COMPLETE LOSS OF THE ATS FUNCTION IS CONSIDERED A FAILURE TO THE 

GE-AVE M/A SYSTEM EVEN THOUGH A FUNCTIONALLY REDUNDANT MODE EXISTS 

TO ACHIEVE MOST OF THE MOL OBJECTIVES 

• PROBABILITY THAT ONE OF TWO ATS IS PERFORMING SHALL BE 0.999 

• RELIABILITY REQUIREMENT FOR EACH ATS SHALL BE 0.98 

• BLOCK AND/OR FUNCTIONAL REDUNDANCY WITHIN EACH ATS SHALL BE UTILIZED 

TO MEET THE 0.999 REQUIREMENT 

• THE DESIGN SHALL BE SUCH THAT NO SINGLE FAILURE WILL CAUSE LOSS 

OF BOTH ATS SUBSYSTEMS 

• CREW SHALL BE UTILIZED TO PERFORM BACKUP CONTROL, LIMITED MAINTAINABILITY 

AND DIAGNOSTIC ANALYSIS WHEN SYSTEM EFFECTIVENESS IS ENHANCED. 

328 

-if-&RE-T--- SPECIAL ANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 --SEC-R-EL SPECIAL HANDLING 

ATS* 

No. 1 

ATS* 

' No. 2 

PATH A 

Meml••■• 

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SYSTEM 

PATH STATE 

ATS 

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i.e., NETHER ATS 

OPERATING 

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NECESSARY TO PERFORM ACQUISITION 

FUNCTION 

MPSS System Level Reliability Diagram 

329 

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- CONTINGENCY MODES - / DEGRADED MODES 

FUNCTIONAL FAILURE 

- LOSS OF CUE DISPLAY 

- LOSS OF ONE ATS 

- RATE GYRO - 

- LOSS OF COOLING LOOP 

- MAGNIFICATION CONTROL 

ZOOM CONTROL 

- LOSS OF ALPHA-NUMERIC 

- LOSS OF DEROTATION 

- LOSS OF PERIPHERAL DISPLAY 

OPERATIONAL MODE 

- CONTINUE ATS SURVEILANCE UTILIZING 

ASTRO. KNOWLEDGE TO IDENTIFY 

ACTIVITY ON TARGETS PRESENTED IN 

ATS FOV 

- GO TO SINGLE OPERATOR MODE, 

SPECIALIST 

- UTILIZE POSITION LOOP 

- MAJOR FAILURE 

- LEAKAGE WILL EFFECT COLD PLATES 

AND ABORT/ABBREVIATE MISSION. 

- MANUAL OVERRIDES WITH LITTLE OR 

NO DEGREDATION 

- LOSS OF REDUNDANT INFORMATION TO CREW 

- MANUAL OVERRIDE ON PRISM 

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MENTAL COUNTDOWN 

331 

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HMEA VDP 

ITEM NUMBER: HEAT SINK 

ASSUMED FAILURE: LOSS OF COOLANT 

POSSIBLE CAUSES: VIBRATION, SHOCK, OVERSTRESS (DURING LAUNCH) 

SYMPTOMS AND CONSEQUENCES: 

MINOR DEGRADATION IN VDP DISPLAYS 

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DESIGN MARGIN AND OVER-PRESSURE TEST 

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DAC MONITORS PRESSURE 

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PROBABILITY OF FAILURE: LESS THAN 1 PER 106 MISSIONS 

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MOL: POTENTIALLY IV 

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PROBABILITY OF FAILURE: NEGLIGIBLE WITH CORRECTION 

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POSSIBLE CAUSES: SPRING, SENSING 

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SOLAR IMPINGEMENT - SAFETY HAZARD TO ASTRONAUT 

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CONSEQUENCES: CREWMAN 

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COMPENSATING AND IDENTIFYING INHIBIT AREAS 

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PROBLEM AREAS 

L/S MAINTENANCE OF 

1. SCANNER 

2. TELESCOPE 

3574358 

SPECIIL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

EFFECTIVENESS = f (QUANTITY, QUALITY) 

QUALITY 

. REQUIRES ONLY ONE ATS AND P.O. FOR BORESIGHTING 

NO LOSS IN QUALITY 

QUANTITY 

. CAPABILITY EXISTS FOR SWITCHING THE PROGRAMMED TARGETS FROM 

ONE ATS TO THE OTHER 

. PROB OF AN ACTIVE CLOUD FREE TARGET - 2,4% 

- PROB OF AN ACTIVE TARGET 6% 

- PROB OF CLOUD FREE TARGET 40% 

. PROB OF USING ATS 2 FOR ACTIVE TARGETS - .5% 

- ATS 1 AND ATS 2 LOOK AT TARGETS WITHIN A 1 - 2° AVERAGE 

ROLL ANGLE DIFFERENCE 

- THEREFORE A TWO DEGREE OR 50% OVERLAP EXISTS 

- IF ATS-1 HAS CLOUD COVER THEN 50% OF ATS-2 FOV HAS CLOUD 

COVER 

. EXPECTED NUMBER OF ACTIVE TARGETS ON ATS-2 - 22.5 TOTAL MISSION 

- BASED UPON 90° ORBIT (CAPT. MCCLAYS) 

- 5000 TARGETS IN ATS 2 FOR 30 DAYS 

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RELEASE 1 JULY 2015 

ALPHA SUBSYSTEM 

DRIVE K GYRO 

. ON/OFF OPERATION IS PLANNED 

OPERATING TIME 131 HOURS 

INCLUDING 12 MINUTE WARM-UP 

PERIODS 

HONEYWELL FORESEES NO PROBLEM 

ASSOCIATED WITH ON/OFF OPERATION 

ADEQUATE DEMONSTRATION MUST 

BE PROVIDED DURING DEVELOPMENT, 

QUALIFICATION AND PRODUCTION 

TESTING 

. GYRO FAILURE RATE IS NOT AFFECTED 

DUE TO ON/OFF OPERATION (BASED UPON 

ABOVE DEMONSTRATION.).PROBABILITY 

OF FAILURE IS REDUCED. 

NOTE: DOCUMENTATION OF VERBAL RESPONSE 

TO QUESTION BY F. HOWARD 

362 

S SPE CL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

PROBLEMS AND UNRESOLVED AREAS 

363 

SPECIAL HANDLING 
PITCH VEHICLE 

ROTATION 

+700 

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(62.3%) 

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364 

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SCANNER CAGING AND STOW TECHNIQUE DURING GROUND, LAUNCH, AND 

ORBITAL ENVIRONMENT APPROACHES INCLUDE: 

A. MECHANICAL LATCH 

B. MAGNETIC CLASP 

C. ACTIVE CAGING THROUGH ENCODER 

D. PYROTECHNIC 

SIZING OF ANY TECHNIQUE COMPLICATED BY ROLL GIMBAL UNBALANCE 

• 

365 

SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL, HANDLING 

THERMAL DUTY CYCLE SPECIFIED UPON ITEK 

A. ASSUMES SEVERE OPERATIONAL RESTRICTIONS 

B. SHOULD BE EXPANDED TO INCLUDE DUMPING HEAT TO COLD 

EARTH OR SPACE 

C. ANALYSIS MUST STILL BE PERFORMED TO IDENTIFY 

OPERATIONAL RESTRICTIONS IF ANY. 

366 

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VENTING OF OBJECTIVE/WINDOW AIR SPACE 

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B. SOLUTIONS: 

1. MANUAL VALVE REQUIREING CREW ACCESS 

2. SOLENOID VALVE 

3. CALIBRATED LEAK 

367 

----S-EeRr SPECIAL HANDLING 
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ACTS/WASTE PROTECTION WHILE SHROUD IS OPEN 

A. EVALUATE IMPACT AT TULAHOMA TEST 

B. OBTAIN IF AGREEMENT WITH DAC FOR INHIBIT 

SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 ---S-FeRfr SPECIAL HANDLING 

VALUE ENGINEERING CHANGE PROPOSAL 

SUGGESTION: 

REASON: 

IMPACT: 

SAVINGS: 

ELIMINATE VDP MANUAL FRAME SELECTOR 

DUPLICATION OF FUNCTION PROVIDED BY 

KEYBOARD 

NONE 

$100,000 ROM 

369 

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• PROTOTYPE HARDWARE 

• SOFTWARE 

▪ INTERFACES 

• PERFORMANCE VERIFICATION 

▪ LIMITED EMI 

• POWER USAGE & INTERRUPT 

DSS 

375 

----SIMET---,SPECIAL HANDLING 
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RELEASE 1 JULY 2015 

SPERAL HANDLING 
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--SteitET- SPECIAL HANDLING 

DISTRIBUTION 

G. S. Hall R. Chamberlin 

C. E. Eastwood R. Scoles 

u/. R. W. Hess H. Jackson 

W. Ussler L. Crandall 

G. Hughey A. Kohn 

L. Huggins J. Frey 

M. Peterson R. Knecht (7) 

F. Nistico W. Heil 

G. Ryan Library (3) 

J. Biog&n 

G. O'Brien 

J. McGuckin 

R. Barchet 

S. Hobbs 

G. Stocking 

E. Ernst 

T. Hooker 

W. Manley 

H. Boys 

G. Christopher 

D. Smith 

P. Connaught 

S. Cheney 

377/378 

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