A Case Study in NASA-DoD - The Black Vault

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i -47- orbit-adjust module, while the SAGE configuration includes a second momentam wheel and a tape recorder. F r Air Force use, the SAGE configuration was selected as being most appropriate. The only modifications that were considered relate to the conversion of the communication system to make it SGLS-compatible. These changes are itemized below and discussed in detail in Appendix C. Basically, the changes involve replacing some of the AEM communication ,0 equipment with the appropriate STPSS communication equipment. o Replace S-band transmitter with STPSS S-band (SGLS) transmitter. o Replace S-band transponder with STPSS S-band (SGLS) transponder. o Replace command demodulator with STPSS dual signal conditioner. o Modify pulse code modulation (PCM) encoder for dual baseband. o Modify command decoder/processor. Although the power system of the AEM is very limited ("'50 W), no changes were made in this system for Air Force use. Also, the nonredundant design of the AEM was unaltered. In addition, the current AEM design does not allow for the use of encryption equipment--this was not changed because it is not a requirement for all Air Force missions considered in this study. STPSS Each of the three available STPSS configurations (summarized in Table 2) consists of a core and an orientation module (or a spin-control module in the STPSS-S case). In addition, a variety of mission-specific equipment is available for each configuration. The core module is the same in all cases. The orientation or spin module determines the attitude stability and pointing accuracy of the spacecraft. The configurations used in this study are those identified by TRW in their study.( I )
-48- No changes were made except, by direction of the Air Force, the hydrazine reaction control system (RCS) designed by TRW for the STPSS was not considered in this analysis because of its relatively high cost compared with the cold gas reaction control system/solid rocket option. Table 2 STPSS CONFIGURATIONS STPSS-P STPSS-LC STPSS-S Core Module Core Module Core Module + + + Orientation Module Orientation Module Spin Control Module e 3-axis e 3-axis . Spin 9 Precision (±0.1 deg) * Low cost (±1 deg) * Low cost (±1 deg) e 1 deg freedom solar e 1 deg freedom * Cold gas RCS drive solar dr. * Cold gas RCS * Cold gas RCS + + +- Mission-Specific Mission-Specific Mission-Specific Equipment Equipment Equipment e Solar panels (max. Same choices as Same choices as for 1200 W1 for STPSS-P. STPSS-P, except e Extra 10 tape 9 Solar panels recorder (max. 380 W) * Encryption unit (GFE) * Orbit transfer module (solids or IUS) e Antenna
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LEYEL r o R-2619-RC May 1980 Standa
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SECUNITY CLASSIFICATION OF Twa PAGE
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Standard 5pacecraft.ProcurementL_ A
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-ivas representing the official vie
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the missions required. Third, the p
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ACKNOWLEDGMENTS I gratefully acknow
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-xii- VI. APPLYING THE NASA-DOD COO
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-. - am~rumn -xv- TABLES 1. Nominal
Page 18 and 19: -Xvii- 11-19. Case IV(N)...........
Page 20 and 21: -xx- L-ANX - Large Diameter Applica
Page 22 and 23: -1- I. INTRODUCTION The National Ae
Page 24 and 25: -3- development. Finally, the polic
Page 26 and 27: -5- of which spacecraft would enabl
Page 28 and 29: -7- II. U.S. SPACE PROGRAM: DEVELOP
Page 30 and 31: -9- thought. (8 ) The launching of
Page 32 and 33: -1- had shown great alarm or acknow
Page 34 and 35: -13- for other purposes. ,(15) it w
Page 36 and 37: -15- and that determination as to w
Page 38 and 39: -17- program and the coordination o
Page 40 and 41: t -19- legislation, messages, petit
Page 42 and 43: -21- of the continuing Soviet accom
Page 44 and 45: -23- Subsequently, the Director of
Page 46 and 47: -25- to be asked by one of the agen
Page 48 and 49: -27- space systems; operational sys
Page 50 and 51: -29- no near-earth orbit manned ope
Page 52 and 53: ImP, ~ ~ ~~~~ ......... ~~~~~~~~~~~
Page 54 and 55: -33- 5. Using off-the-shelf, space-
Page 56 and 57: -35- 1. Spacecraft configurations a
Page 58 and 59: -37- STANDARD SPACECRAFT DESCRIPTIO
Page 60 and 61: -39- The payload cluster, while uni
Page 62 and 63: -41- payload or propulsion, is abou
Page 64 and 65: -43- z z 0 0 - 0r CL 0 E 4 41- u- 0
Page 66 and 67: -45- The STPSS can carry a nominal
Page 70 and 71: -49- M9IS The basic MMS, summarized
Page 72 and 73: -51- 1980-1990 time period are divi
Page 74 and 75: -53- about 7.5 payloads per spacecr
Page 76 and 77: -55- 0- - - - - - - - - - cc - - -
Page 78 and 79: -57- STPSS (STPSS-LC) spacecraft ca
Page 80 and 81: -59- Table 7 ESTIMATED UNIT 1 COST
Page 82 and 83: -61- Nonrecurring Costs. Nonrecurri
Page 84 and 85: -63- where SRU = Service Rendered U
Page 86 and 87: -65- IV. STANDARD SPACECRAFT ACQUIS
Page 88 and 89: -67- The costs associated with thes
Page 90 and 91: -69- to increase to 13. That was fo
Page 92 and 93: -71- 500 * STPSS 400 AW-STPSS PROGR
Page 94 and 95: -73- The implications of the forego
Page 96 and 97: -75- option. Other candidates becom
Page 98 and 99: -77- the Air Force's Space Test Pro
Page 100 and 101: -79- decrease any total program cos
Page 102 and 103: -81- COST LAUNCH COSTS (Millions of
Page 104 and 105: -83- V. NASA-DOD COOPERATION: ORGAN
Page 106 and 107: -85- the MHS program stemmed from t
Page 108 and 109: -87- The Air Force had studied the
Page 110 and 111: -89- Air Force Headquarters to NASA
Page 112 and 113: -91- turns out, NASA had agreed to
Page 114 and 115: also evaluate whether or not adequa
Page 116 and 117: -95- design, mission model, cost es
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-97- Force interface was retained,
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-99- experience and by identifying
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. . . . . . . -.. . . . . . . . . .
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-103- the nation and other governme
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-105- Appendix A ESTIMATES OF COST
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-107- RANGE OF BIDS Item Range ($ t
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-109- Table A-1 SPACECRAFT COSTS--N
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'I FI Table A-2 SPACECRAFT COSTS WI
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-113- Table A-3 LAUNCH COSTS--NOMIN
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-115- Table A-5 LAUNCH COSTS FOR TH
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Table B-I POWER SYSTEM COMPARISONS
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-119- NOTES TO TABLE B-I (Cont.) mo
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-121- The duration of the data pass
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-123- INNNU AWA n -. s vo (I T 'API
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-125- each battery has its own char
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-127- Table B-2 POWER SUMMARY Chara
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-129- Appendix C COMMUNICATIONS AND
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-131- chiefly for storing commands
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-133- Table C-2 C&DH CHANGES REQUIR
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-135- Table C-3 C&DH CHANGES REQUIR
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-137- NOTES TO TABLE C-3 (Cont.) we
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- 139- Table D-1 ATTITUDE CONTROL A
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* -141- and three reaction wheels a
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-143- by the commonly adopted desig
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-145- Table E-l--Continued I Unit T
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-147- flight-proven elastomeric dia
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-149- Appendix F STRUCTURAL SUBSYST
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-151- points are provided by three
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-153- Table F-2 STPSS STRUCTURAL CO
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-155- Appendix G THERMAL CONTROL SU
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-157- sunlight. These surfaces incl
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-159- Appendix H PROGRAM OPTIONS FO
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I 4 I IQ. w ~ w 01 " 1 I I I I 0 .c
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-163- Table H-4 ORBIT 2: PAYLOAD AS
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-165- c0 k- c" Q N 3- W 0 0 IT -- c
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-167- Table 1-7 CASE I (A)a PROGRAM
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-169- Table H-9 CASES I (K) AND V (
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-171- Table H-11 CASE II(B) PROGRAM
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-173- Table H-13 CASE 111(C) PROGRA
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-175- Table H-15 CASE 111(M) PROGRA
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-177- Table H-17 CASE IV(D) PROGRAM
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-17 9- Table H-19 CASE IV(N) PROGRA
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-181- Table Hi-21 CASE V (E) PROGRA
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-183- Table H-23 CASE VI(F) PROGRAM
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-185- Appendix J AIR FORCE AND NASA
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MEMORANDUM OF AGRE1MENT ON THE PROC
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-189- 2.2 DOD SPACE TEST PROGRAM: T
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-191- l4.1.7 STP will review the HF
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I -193- 5.0 NASA AND DOD FINANCIAL
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-195- 5.4.3 Post Delivery Phase: NA
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I '-197- $4 .0 0 A 0 f-4 ;C:ur 0 V
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t 4 In I Io H 0p Ad ~t m 00 -199- E
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-201- COPIED August 24, 1976 Honora
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-204- 13. "The National Space Progr
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-206- 39. Tec hnical vpoaal for a M
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