A Case Study in NASA-DoD - The Black Vault

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-119- NOTES TO TABLE B-I (Cont.) mounted to the six faces of the space vehicle; it should be noted that not all solar cells are exposed to the sun simultaneously on this spacecraft, therefore, about 1200/w of 382 W are available on this design. JElectrical power consumption of the standard STPSS modules, excluding experiments, is determined by the stabilization system used: spinning spacecraft, 92 W; three-axis earth reference, 136 W; three-axis stellar (and wheels), 185 W; three-axis stellar with hydrazine, 197 W. kTRW does not recommend using batteries smaller than 20 Ah for missions requiring less than 500 W because the nonrecurring costs associated with designing a smaller capacity battery and with interface redefinition would increase program cost by about $200K to $300K. Recurring battery cost savings due to using the smaller battery are not substantial, since, typically, cell hardware contributes only 20 percent to battery total cost, with the other 80 percent due to test and quality control requirements. ZExcess power generated by the STPSS solar array is shunted into resistive modules on the surface of the spacecraft and radiated into space. From Ref. 5: mPage 22 says, "28 ±7 V dc negative ground." nThe power subsystem can support an orbital average load of 1200 W in any orbit from 500 to 1665 km and at geosynchronous altitude. This includes being able to accommodate a peak load of 3 kW for 10 min, day or night. These determine the peak and average power requirements of the power regulating unit and batteries. 0 The choice of various numbers of batteries and two sizes allows a large variation in battery capacities to be chosen to suit the particular experiment: 20, 40, 50, 60, 100, or 150 W. PThe most recent specification calls for a 60 percent depth of discharge in synchronous orbit instead of 50 percent. qThe baseline power module weighs about 254 lb, including the case, louvers, and all module attachment hardware. The heat sink louvers, which prevent thermal runaway of the switching semiconductors, weigh 12 to 13 lb. The weight of the power subsystem frame or box, i.e., without electronics, just structure, is about 54 ib; and the attachment hardware is about 25 lb. Thus, the 254 lb power system module, excluding thermal and structural elements, weighs about 262 lb. Each 20 Ah battery weighs about 50 to 53 lb; each 50 Ah battery weighs about 100 to 110 lb. Thus, for the baseline case, the weight of the battery and power conditioning is about 354 lb; and, for 3 x 50 Ah batteries, the total weight can be as much as 585 lb. Note that these figures include some structure but do not include the vehicle harness, i.e., power distribution.
-120- NOTES TO TABLE B-1 (Cont.) rWhile all the batteries are connected to a single power regulator unit, the unit has been designed to compensate for loss of a single cell, or even an entire battery, without jeopardizing the total power system. SNASA Goddard's MS program office has decided to use a peak power tracker rather than the separate battery charging modules, plus shunt modules typically used in direct energy transfer systems. The tracker works by tracking the peak power point of the solar array. When peak power is not required, the power regulating unit forces the solar array operating point to a lower level. Therefore, no excess power is produced which would have to be dissipated. The peak power tracker lends itself to simpler interfaces than the direct energy transfer system with shunt module dissipators. Applications I tC./SAGE CRITUCAL DESIGN REVIEW Expio,., APRIL 7 & 8, 1976 Ioc Systems A v-- M isions DESIGN ADEQUACY soace syS,.s D,.S¢f Godclardl Saace Fiq'n Center ARM PLUGS T.PYRO BUS _____ REGULATOR ZPAN~EL PC~ER SOLAR SOLARAS. PANEL RELAY 1 BOX R VOT1- L.- '' MOT *VOLT. VOLT. AMP-HR. UVIOL SOLAR ARRA: ELECTP.ONICS *SAG[ ,'L t -Fi is rut - M4ETER SENSOR VO n *SAGE ONLY Fig. B-i -Power and distribution subsystem block diagram
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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)...........
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-xx- L-ANX - Large Diameter Applica
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-1- I. INTRODUCTION The National Ae
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-3- development. Finally, the polic
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-5- of which spacecraft would enabl
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-7- II. U.S. SPACE PROGRAM: DEVELOP
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-9- thought. (8 ) The launching of
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-1- had shown great alarm or acknow
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-13- for other purposes. ,(15) it w
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-15- and that determination as to w
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-17- program and the coordination o
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t -19- legislation, messages, petit
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-21- of the continuing Soviet accom
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-23- Subsequently, the Director of
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-25- to be asked by one of the agen
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-27- space systems; operational sys
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-29- no near-earth orbit manned ope
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ImP, ~ ~ ~~~~ ......... ~~~~~~~~~~~
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-33- 5. Using off-the-shelf, space-
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-35- 1. Spacecraft configurations a
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-37- STANDARD SPACECRAFT DESCRIPTIO
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-39- The payload cluster, while uni
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-41- payload or propulsion, is abou
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-43- z z 0 0 - 0r CL 0 E 4 41- u- 0
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-45- The STPSS can carry a nominal
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i -47- orbit-adjust module, while t
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-49- M9IS The basic MMS, summarized
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-51- 1980-1990 time period are divi
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-53- about 7.5 payloads per spacecr
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-55- 0- - - - - - - - - - cc - - -
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-57- STPSS (STPSS-LC) spacecraft ca
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-59- Table 7 ESTIMATED UNIT 1 COST
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-61- Nonrecurring Costs. Nonrecurri
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-63- where SRU = Service Rendered U
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-65- IV. STANDARD SPACECRAFT ACQUIS
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-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,
Page 120 and 121: -99- experience and by identifying
Page 122 and 123: . . . . . . . -.. . . . . . . . . .
Page 124 and 125: -103- the nation and other governme
Page 126 and 127: -105- Appendix A ESTIMATES OF COST
Page 128 and 129: -107- RANGE OF BIDS Item Range ($ t
Page 130 and 131: -109- Table A-1 SPACECRAFT COSTS--N
Page 132 and 133: 'I FI Table A-2 SPACECRAFT COSTS WI
Page 134 and 135: -113- Table A-3 LAUNCH COSTS--NOMIN
Page 136 and 137: -115- Table A-5 LAUNCH COSTS FOR TH
Page 138 and 139: Table B-I POWER SYSTEM COMPARISONS
Page 142 and 143: -121- The duration of the data pass
Page 144 and 145: -123- INNNU AWA n -. s vo (I T 'API
Page 146 and 147: -125- each battery has its own char
Page 148 and 149: -127- Table B-2 POWER SUMMARY Chara
Page 150 and 151: -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
Page 158 and 159: -137- NOTES TO TABLE C-3 (Cont.) we
Page 160 and 161: - 139- Table D-1 ATTITUDE CONTROL A
Page 162 and 163: * -141- and three reaction wheels a
Page 164 and 165: -143- by the commonly adopted desig
Page 166 and 167: -145- Table E-l--Continued I Unit T
Page 168 and 169: -147- flight-proven elastomeric dia
Page 170 and 171: -149- Appendix F STRUCTURAL SUBSYST
Page 172 and 173: -151- points are provided by three
Page 174 and 175: -153- Table F-2 STPSS STRUCTURAL CO
Page 176 and 177: -155- Appendix G THERMAL CONTROL SU
Page 178 and 179: -157- sunlight. These surfaces incl
Page 180 and 181: -159- Appendix H PROGRAM OPTIONS FO
Page 182 and 183: I 4 I IQ. w ~ w 01 " 1 I I I I 0 .c
Page 184 and 185: -163- Table H-4 ORBIT 2: PAYLOAD AS
Page 186 and 187: -165- c0 k- c" Q N 3- W 0 0 IT -- c
Page 188 and 189: -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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A Case Study in NASA-DoD - The Black Vault

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