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V I P 

PRESENTATION 

AUGUST 9, 1967 

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RELEASE 1 JULY 2015 

-•-esiora.F..T—SPECIAL FIAT DLING M-13 

RESOLUTION AND POINTING CONSIDERATIONS (B) 

POINT TO 'BE MADE 

Describe the technologies and key equipments 

required to meet the program requirement. 

. Color code is the same as the previo.as chart. 

. Photographic system design and static optical factors will be discussed in detail by 

Eastman Kodak. 

. Photographic system design factors provide the theoretical performance possible. 

. Lens aperture determines the amount of light capable of being admitted to the camera. 

. Focal length affects theoretical magnification. 

. Film determines the amount of fine detail that can be resolved. 

. Range affects the net resolution that can be achieved in conjunction with the above. 

. Static optical factors define the affect that the hardware has on theoretical. performance 

and is a function of Material quality, workmanship and allowable manufacturing tolerances. 

. Optical quality defines the affect of the glass in distorting the light And reducing 

its intensity. 

. Focus adjustment has tolerances and title introduCes some modification to the 

s:arpness of the image. 

. Contrast of the target will vary and this will affect the amount of detail that 

may be detected. 

. Exposure time has tolerances and thus affects the quality of the image on the film. 

. Optical alignment affects the centering of the incident light on the camera and film 

and tolerances thereon affect performance; • 

Temperature.. control of the optiesandAng,r,Q44ding..atrustureJsrequired,to,keeP 

giass.t distortion to acceptable 

,n. 

. The dynamic characteristics of the vehicle and optics and their control are controlled by l' 

the functions lieted.on the chart. 

. Vehicle attitude rates are controlled by the MoDettell-;Douglas Attitude co,ltrol 

and Translation Subsystem and their magnitudes are transmitted to the computer, 

. Mission computations are ptrformed by the Op4oerd cempUter, which, together with 

data from:the star tracker and the image velocity sensor, provide commands to 

the treating Mirror, controlling its tracking rate. ' • 

In addition, the computer is prOgrammed to control all mission operations, "their 

sequence and timing. 

These may be modified by the p11 t in making corrections and by ground command. 

. Image velocity sensing is necessary, especially in-the automatic mode, to liMit the• 

relative motion of the line-of-sight at the center of the format so that resolution 

is not degraded beyond allowablejimits. Two image velocity sensors, which are 

redundant, will perform this function by sensing this motion, converting it to an 

electrical' signal to the computer, which it turn modifies the tracking mirror rate. 

During manned flights, the pilot may also observe relative image velocity and, through 

his manual controls, reduce it. His corrections, in addition to those provided by 

the image velocity sensor are recorded and transmitted to the ground, where they 

will be used to correct t!,a design-of the image velocity sensor. 

. Vibration of all structural elements Are specified in terms of amplitude and frequency 

limits in order-to limit image motion. within the specified limits, tie trackitg 

mirror control will modify the tracking mirror rate to compensate for vibration, 

utilizing the image velocity sensor, the rate gyros and the computer. 

The crew can also perform this function. 

. The:ipmperattre of the tracking mirror bay and tracking mirror must be maintained 

within close tolerances (70°F ± 5°) to reduce optical distortions to acceptable 

values. The temperature gradient through the tracking mirror must be maintained . 

to 0.1°F per foot or less to assure that its glass surface is flat to within 1/20 

, of a wavelength of light (average). • 

This control must take place under all conditions of sun angle, vehicle attitude, 

during photography when the thermal door is open and during the night side of the 

orbit. 

. Image motion compensation across the format is performed by Eastman Kodak and-corrects 

for differences in the motion of the line-ofrsight away from the center of the format,. 

1 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

The targetting functions are performed by-the functions listed. 

The command and control, ground based computer- program can supply corrections 

to the tracking mirror rate, based on evaluation of t)- eking data, pilot 

observations and other. In addition, the target deck may be changed to allow a 

different--set of targets to'he-progra=ed and-photographed.- Floper-constratms—

are automatically placed on the sequencing of targets to be compatible, with 

vehicle capabilities. 

Target location is prepprogrammed into the on-'oard computer as a table of coordinates 

using geodetic data-and other observations. The sequence of targets to be 

photographed is also preprogrammed. 

Based on direct observations, the pilot can correct the pointing angle of the 

tracking mirror and this correction,. together with orbit imrameters, vehicle 

location, and star tracker data, allows the computer to compute corrected 

coordinates for that target. • 

Navigation combines target location on the ground with vehicle location in orbit. 

Tracking by grov.ld station provides data for periodic updating of orbit parameters, 

which then locates the vehicle with respect to the targets. An on-board drag 

accelerometer provides continuous data on atmospheric drag so that this effect on 

orbit characteristics can be continually updated by the/on board computer and, via 

telemetry, by the Mission Control Center. This information is utilized by the 

vehicle Attitude Control and Translation Subsystem to correct the- orbit by periodic 

firing of its thruster. The computer alsp modifies the pointing commands to the 

tracking mirror based on this data. 

The pilots may play a role in this function by direct observation of the target and 

if required, may correct the tracking mirror attitude by manual control. This 

correction is operated on by the computer and the results serve to improve the 

preprogratLed orbit equations. 

Navigational accuracy, including the on-board drag accelerometer, require that the 

vehicle be located to within 0.1 nautical mile of a predetermined position 4 

orbits in advance. With the pilot, - this accur-cy can be with reference to a 

given target. 

System alignment concerns the alignment between the star tracker and the 

tracking mirror and between the primary optics and the tracking mirror. Changes 

. in alignment are sensed by an electro-optical device and sent to the computer 

which modifies the tracking mirror attitude, 

The pilot participates in this function by direct observation of alignments and 

changes in the centering of the target and can manually make corrections. 

Tracking mirror attitude is a result .of the above considerations and is ccliputed 

on board and commanded by the computet, This is performed -automatically,' 

using navigation, target location, star tracker and vehicle attitude data. The 

pilot can make manual corrections if required MANULIMJ 
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_g_Zie..d..._ /IEELIES AND BRIEFINGS RETIRED FILE 

DATE 

L.de- ezeaft • 1./ pa;r!,;-?m / • 

r.rirf n- t- i; a uirit..?1,.! 

• 1441'.5 6 

Et: titre! Systeta 

68308-69 

89624-69 

68354-69 

21307-67 

50196-67 

21383-67 

21218-67 

21171-67 

21138-67 

21384-67 

1.O 21009-67 

Uncl 

CH 4206 

21310-66 

ye/ WH 5507 

7170-66 

21132-66 

21099-66 

21092-66 

SUBJECT 

13 May 69 MOL Policy Committee Meeting - 9 May 69 

11 Feb 69 Brief - MOL & VHR Issues Given DepSecDef 

14 Sep 67 Report of 14 Sep DORIAN Brief for Sec of Def 

9 Aug 62,,,VIP Presentation 

Undtd. General Stewart's Presentation 

J

ul 67 Minutes, Jul 7 Internal Management Meeting 

12 Jun 67 DORIAN Status Briefing to Dr. Hornig 

14 Apr 67 Minutes, 14 Apr 67 MOL Management Meeting 

14 Mar 67 Meeting on MOL Revised Costs/Schedules 

16 Jan 67 5 Jan 67 MOL Management Meeting 

9 Jan 67 Action Items fr Last MOL Program Review 

9 Jan 67 Guidance/Decisions fr MOL Management Meeting 

17 Aug 66 Briefing to PSAC on MOL 

21 Jul 66 Proposed Agenda for PSAC 

7 Jun 66 Wholly Unmanned System Briefing 

13 May 66 EKC Visit on 17 May w/66692-66 Ser A cy 2 

13 Apr 66 PRC, MOL Systems Office, Apr 2, 66 

5 Apr 66 PRC, MOL Systems Office, 2 Apr 66 

NO. NO. DATE 

/5- 

4- Apr 69 Briefing to Dr. McLucas by Gen Bleymaier Of $APRR 

ttt ,f)cl- Undtd AF MOL Policy Committee Agenda Item-1st 

Meeting 2-25-65, AYCmi,r /1-7-C17:077 

20. 65-0910-A2 

” 36.687765 

- 1 • • 

,'""`r! • ; 

2 Mar 65 MOL Policy Committee Meeting 

6 Jan 65 Meeting with Dr. McMillan on 10Li 1A-)k Mrifre, 

R -7"/V0e ./t//$1 7- ie. 11,L.,..<_