A Case Study in NASA-DoD - The Black Vault

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-149- Appendix F STRUCTURAL SUBSYSTEI: A COMPARISON OF AEM, STPSS, AND 101S by M. M. Balaban AEM STRUCTURAL SUBSYSTEM The principal elements of the AEM ( 3 1 ' 3 6 ' 3 7 ) structural subsystem that are of interest for a shuttle application consist of a base module and an instrument module. The base module structure contains support subsystems for the HC M and SAGE missions, including all appendages and mechanisms to support these subsystems. The differences between these missions have no effect on the primary structural subsystem. The base module consists of an 18 in. long hexagonal body with six longerons tied to a 7 in. conical structure that mates with a standard Scout series 25E adapter. Open truss bulkheads rigidize each end of the hexagonal enclosure. This design provides approximately 7.3 sq ft of usable flat surface for experiment mounting. The structural elements of the base module are primarily sheet and stringer aluminum. Side panels of the hexagon are 0.012 in. thick clad 2024-T3 aluminum sheet riveted to the six corner longerons. Panel edge members, equipment support stiffeners, and truss-type bulkheads are also formed from 2024-T3 aluminum sheet. The longerons are standard Burner IIA extrusions, specifically shaped for hexagonal structure corners. The truss-type bulkheads at either end of the hexagonal body provide structural rigidity, with good accessibility to the interior. These bulkheads are 2024-T3 formed parts attached to the body longerons. The forward bulkhead ties to the four longerons that serve as attach fittings to the instrument module. The center diagonal is easily removed by disconnecting fasteners at each end so as to provide better access for installing or removing interior components. The aft bulkhead supports the modular orbit-adjust system tor HCM missions. The orbit-adjust system, which is fabricated, tested, and serviced as a separate module, is bolted to the aft bulkhead at three points. Shims are bonded to the aft bulkhead to provide proper
-150- lateral and angular alignment once the spacecraft mass properties have been determined. The instrument module contains the mission instruments and the supporting electronics. This module is connected by low-heat-conduction, bolted-in fittings at four of the six longeron forward ends so as to provide direct load transfer. Fiberglass blocks and thermal blankets reduce heat conduction to less than 0.2 W/°C. This type of attachment fitting was used in the Burner IIA and P42-I units. The four structural attach points feed acceleration loads directly into the base module longerons. The total weight of the AEM structural subsystem is 47.7 lb, consisting of 27.2 lb of primary structure, 17.5 lb of secondary structure, and 3 lb of mechanisms. IMS STRUCTURAL SUBSYSTEM The primary structural elements of the MMS ( 3 8 ' 3 9 ) for shuttle operation are the module support structure and the transition adapter. The power, attitude control and stabilization, and C&DH module skins are secondary structural elements in that they support elements of the spacecraft subsystems. Module Support Structure The module support structure provides structural continuity between the transition adapter, subsystem modules, and propulsion module. Its construction is basically a three-dimensional truss, with the six corners as the primary load points. (Electrical connectors and other insignificant loads may be hung on the struts themselves.) The Rockwell technical proposal for fabrication shows the structural elements to be primarily sheet, angles, and channels. The corner fittings appear to be 60 deg V-shaped channels especially designed for triangular corners. Transition Adapter The transition adapter is the interface between the module support structure and the mission adapter. During shuttle boost, it is also the element that connects to the flight support system. The attachment
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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
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-69- to increase to 13. That was fo
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-71- 500 * STPSS 400 AW-STPSS PROGR
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-73- The implications of the forego
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-75- option. Other candidates becom
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-77- the Air Force's Space Test Pro
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-79- decrease any total program cos
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-81- COST LAUNCH COSTS (Millions of
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-83- V. NASA-DOD COOPERATION: ORGAN
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-85- the MHS program stemmed from t
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-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,
Page 120 and 121: -99- experience and by identifying
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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 140 and 141: -119- NOTES TO TABLE B-I (Cont.) mo
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 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
Page 190 and 191: -169- Table H-9 CASES I (K) AND V (
Page 192 and 193: -171- Table H-11 CASE II(B) PROGRAM
Page 194 and 195: -173- Table H-13 CASE 111(C) PROGRA
Page 196 and 197: -175- Table H-15 CASE 111(M) PROGRA
Page 198 and 199: -177- Table H-17 CASE IV(D) PROGRAM
Page 200 and 201: -17 9- Table H-19 CASE IV(N) PROGRA
Page 202 and 203: -181- Table Hi-21 CASE V (E) PROGRA
Page 204 and 205: -183- Table H-23 CASE VI(F) PROGRAM
Page 206 and 207: -185- Appendix J AIR FORCE AND NASA
Page 208 and 209: MEMORANDUM OF AGRE1MENT ON THE PROC
Page 210 and 211: -189- 2.2 DOD SPACE TEST PROGRAM: T
Page 212 and 213: -191- l4.1.7 STP will review the HF
Page 214 and 215: I -193- 5.0 NASA AND DOD FINANCIAL
Page 216 and 217: -195- 5.4.3 Post Delivery Phase: NA
Page 218 and 219: 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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