A Case Study in NASA-DoD - The Black Vault

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- 139- Table D-1 ATTITUDE CONTROL AND STABILIZATION SYSTEMS STPSS Characteristic% and Specifications AEM I II III M S Type of Precision Precision Stabilization Three-Axis Spin Three-Axis Three-Axis Three-Axis Performance: Attitude control ±16 pitch, 1*-2 1-20 0.10 Less than roll spin axis all axes all axes 0.010 ±2* yaw all axes Rate control ±0.01*/sec 0.01*/sec 0.003*/sec Less than all axes 10-6*/sec all axes (long term) Attitude ±0.50 0.20-0.4* 0.020 determination pitch, roll ±20 yaw Control Torques: RCS None Cold gas, Cold gas, N 2 ; N 2 H 4 Hydrazine N 2 N 2 option (optional) Momentum wheels Pitch bias None None 3, re- 4, reaction wheel, roll action wheels wheel option Electromagnets 3 None Option Option 3, pitch, roll, yaw Nutation damper None 1 None None None Sensors: Earth Mounted on 1 2, conical None None pitch wheel scan Sun 3 head sun 1 2 2 Both fine sensor and coarse (solar array) Star None None None 2 strapdown 2 strapdorn trackers trackers Magnetic 3 axis None Option Option 3 axis magnetometer magnetometer Gyros None None 2 rate 4 rate 3 axis + (I standby) redundancy Accelerometers 1 None None None None Miscellaneous: Computer Minimal None Yes, dedi- Yes, dedi- Yes, shared cated cated Control system weight 29 lb 95 lb 165 lb 289 lb 253 lb (not including N2 1 RCS weight) ILL
-140- The AEM attitude control system does not include reaction jets as a means of torque generation. Thus there are no limits on operational lifetimes due to fuel considerations. However, magnetic torques are relatively weak and as a consequence control time constants tend to be large--on the order of an orbital period. Also, magnetic torques decrease with increasing altitude and for the AEK design, they become ineffective for altitude in excess of 1000 n mi. The simplest of the STPSS designs utilizes spin stabilization. Thus, ideally, the spin axis of the vehicle is inertially fixed. No provisions are made for a despun platform. A mechanical nutation damper is provided to remove unwanted spin axis wobble and cold gas jets are used to reorient or stabilize the direction of the spin axis. Sun and earth sensors are used for attitude determination. The second STPSS design is a low-cost, three-axis system with performance specifications similar to those of the AEM spacecraft (see Table D-l). The attitude control system of this version of the STPSS differs from that of the AEM in that a pitch momentum wheel is not used to provide roll-yaw stabilization and cold gas reaction jets are the primary means of generating control torques. Two conical scan earth sensors provide pitch-roll attitude information, while a rate gyro is used to detect yaw attitude errors. Since, without a pitch momentum wheel, this version of STPSS does not have any inherent stability, disturbances from either internal or external torques must be countered by the reaction control system. For low altitude orbits where aerodynamic and gravity gradient disturbance torques can be large, control system fuel requirements for a one-year mission might be excessive. This situation could be alleviated by adding electromagnetic torques and a magnetometer to the control system so that almost continuous use of the reaction jets would not be necessary. The third version of the STPSS is designed to attain precise pointing accuracies and rate control. To improve performance relative to the low-cost three-axis design, two star trackers, two rate gyros, In essence, the body of the AE4 spacecraft Is a despun platform with the pitch wheel inertially stabilized. AL
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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
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 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 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
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
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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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