A Case Study in NASA-DoD - The Black Vault

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-63- where SRU = Service Rendered Units, which may not exceed 100. It represents a percentage of total launch cost. Length is in feet, weight in pounds, inclination in degrees, and altitude in nautical miles. If the SRU exceeds 100 ft it is assumed to be truncated at 100. A formula proposed since the earlier phase consists of prorating the dedicated shuttle cost on the basis of whichever of the load-factor ratios below is larger: 1. payload length (in feet) 60 2.* payload weight (in pounds) shuttle orbital capacity (in pounds) to the desired inclination and altitude In this study, we have assumed a direct relationship between load factor, as determined above, and the cost factor for prorating the dedicated shuttle cost. In some formulations of this tariff rate, the load factor is multiplied by as much as a 1.4 cost factor; this has not been used in this study. Because the launch cost is very sensitive to payload length when using this NASA tariff, an attempt was made to minimize launch cost by placing payloads laterally rather than longitudinally in the shuttle bay whenever the payload length was less than 13 ft. Launch costs estimated using the above method are identified as the modified NASA tariff. The other cost-allocation schemes considered were: a full allocation by weight, i.e., Private conversation with Mr. Edwin G. Dupnick at the Johnson Space Center of NASA, October 1916. Payload length is the sum of the lengths of the Space Test Program payload, spacecraft, and solid kick stages. For this study, nominal shuttle capacities of 65,000 lb for ETR lainches and 39,000 lb for WTR launches have been used. A nominal altitude of 150 n mi has been used. Solid rocket kick stages are used to translate the spacecraft to higher orbits. Payload weight is the um of the weights of the Space Test Program payload, spacecraft, and kick stages.
-64- payload weight shuttle orbital capacity x $15.4 million plus a service charge of $1 million; an allocation of only half the shuttle cost plus a service charge; and, a service charge only. Kick Stages A variety of solid propellant kick stages were required, and to simplify the task of assigning a cost to each kick stage a simple cost-estimating relationship was derived from the cost of several existing stages: C = 2900 W " where C = stage cost in 1976 dollars, and W = stage weight (lb). Where the IUS was used, a cost of $4.3 million was charged.
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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
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 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 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,
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
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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
Page 204 and 205:
-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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