A Case Study in NASA-DoD - The Black Vault

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-39- The payload cluster, while unique for each set of payloads, has a common mechanical, thermal, and electrical interface with the STPSS. As can be seen in Fig. 1, the configuration of the solar cells is different for the three-axis- and spin-stabilized versions of the STPSS. These panels are also -modular, thereby allowing the electrical power generated by the spacecraft to be tailored to the payload demand. The three-axis-stabilized version of the STPSS has a dry weight of about 1000 lb without payload or propulsion system. It is about 7.5 ft in diameter, and about 32 in. thick. One of the reasons behind this "pancake" design was to minimize the length of the spacecraft so that it would fit into the space shuttle without occupying primary bay space, allowing the Space Test Program missions the option of flying on board the space shuttle as a secondary payload. The MMS design, depicted in Fig. 2, consists of a centrally located triangular-shaped module support structure having attach points for: (1) the power module, (2) the attitude control and stabilization (ACS) module, (3) the communications and data handling (C&DH) module, (4) the mission adapter-payload module, and (5) either a small or large impulse propulsion module. In this design, all missions are flown with the first four modules; the propulsion module is optional, depending on the mission. For missions requiring large orbital transfers, either the IUS or other appropriate solid motors replace the propulsion modules shown in Fig. 2. As will be discussed later in this section, several equipment options are available within each of the three main modules (power, ACS, and C&DH) to accommodate mission-specific requirements. For example, the solar array design shown in Fig. 2 is generally considered to be similar to that of the stabilized version of the STPSS. Again, it is modular and may be tailored to the mission power requirement. The MMS is designed for remote on-orbit replacement and servicing and, as a result, is a much more sophisticated design than the STPSS. The payload interface (power, thermal, mechanical, and data handling) is constant for all missions. The NMS weighs about 1400 lb without the solar array or space propulsion system. The overall width is about 4.5 ft and its length, without
-40- PAYLOAD SHUTTLE CAPTURE DROGUE TRANSITION ADAPTER SMALL IMPULSE POWER MODULE I ExplodedPROPULSION MODULE SOURCE: Ref. 5. Fig. 2-Modular multimission spacecraft
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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
Page 10 and 11: the missions required. Third, the p
Page 12 and 13: ACKNOWLEDGMENTS I gratefully acknow
Page 14 and 15: -xii- VI. APPLYING THE NASA-DOD COO
Page 16 and 17: -. - 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 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 68 and 69: i -47- orbit-adjust module, while t
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
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-89- Air Force Headquarters to NASA
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-91- turns out, NASA had agreed to
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also evaluate whether or not adequa
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-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
Page 152 and 153:
-131- chiefly for storing commands
Page 154 and 155:
-133- Table C-2 C&DH CHANGES REQUIR
Page 156 and 157:
-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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