A Case Study in NASA-DoD - The Black Vault

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-49- M9IS The basic MMS, summarized in Table 3, consists of three primary modules, plus a variety of mission-specific equipment, all of which are attached to a structural subsystem. For Air Force use (1) the attitude control module is retained without modification, (2) one 20 Ah battery is added to the power module so that it would have the same Table 3 MMS CONFIGURATIONS MMS MMS-AF Attitude Control Module + + Power Module e Two 20 Ah batteries + + Attitude Control Module Power Module e Three 20 Ah batteries C&DH Module C&DH Module * TDRSS- and STDN-compatible e SGLS-compatible + * [Data rate 128-256 kbps]a Mission-Specific Equipment + e Antenna Mission-Specific Equipment * Solar panels (as required) Same as above, exccept 9 Space propulsion (SPS-I, e Solid rockets for orbit SPS-II, IUS) translation * Solar drive o Extra tape recorders (8 x 10 9 bits) * Extra batteries (one 20 Ah or three 50 Ah) aAdditional option.
-50- energy storage capacity as the STPSS, and (3) the communications system is changed to be compatible with SGLS. Listed below are the detail modifications to the MMS communication module needed to achieve this compatibility. Again, these modifications consist mainly of replacing MMS communication equipment with STPSS equipment that performs a similar function. The necessary changes to increase the data rate to 128-256 kbps have not been considered as requirements. SGLS Compatibility a Replace S-band transponder with STPSS S-band SGLS transmitter and receiver. * Replace or modify command decoder with STPSS decoder. * Replace premod processor with STPSS dual baseband unit. Increase Data Rate * Replace data bus controller ) with STPSS bus " Replace clock and format generator controller (data * Replace standard computer interface formatter). * Replace remote interface unit with STPSS data interface unit. Although the parallel battery-charging design used in the MMS power module has been of some concern to the Air Force, it was not considered necessary to change it (see Appendix B), since the power regulation unit will have adequate redundancy to meet Air Force requirements, and the MMS power system will be a flight-proven design before the missions considered in this study are undertaken. SPACE TEST PROGRAM MISSION MODEL In accordance with the directions provided by the Work Statement for this study, Space Test Program missions (26) to be flown during the It should be noted that if the Air Force Solar Infrared Experiment (SIRE) is flown on the MMS, these changes in the communication module will have already been made before any of the missions considered in this study. As noted later in this section, the MMS cost estimates are based on this assumption, hence the nonrecurring cost associated with these changes is not included in the study.
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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
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-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 68 and 69: i -47- orbit-adjust module, while t
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
Page 118 and 119: -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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