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General Disclaimer One Or More of the Following Statements May Affect This Document General Disclaimer One or more of the Following Statements may affect this Document This document has been reproduced from the best copy furnished by the organizational source. It is being released in the interest of making available as much information as possible. This document may contain data, which exceeds the sheet parameters. It was furnished in this condition by the organizational source and is the best copy available. This document may contain tone-on-tone or color graphs, charts and/or pictures, which have been reproduced in black and white. This document is paginated as submitted by the original source. Portions of this document are not fully legible due to the historical nature of some of the material. However, it is the best reproduction available from the original submission. Produced by the NASA Center for Aerospace Information (CASI) f , 0 44)Y^ R'I (NA$A --C 4 -1737 65) EXCESS SCIENCE N84-;18882 IiCLU4i'lUlitlT,Ut CAPABILITIES ANC EXCESS PE1t2uL4ANCE CAPABIL,1TIES ASSLSSMEN1 FOR MARS UL0jC16iiLE AND (L ,I.PIA`1'ULW Y ORBIT L;11: U1XC-Ld 3 .,X'r.jNI)Jll STUDY F ival Hoport (ACA Government; GJ/1l 17782 Excess Science Accommodation Capabilities and Excess Performance Capabilities Assessment for Mars Geoscience and Climatology Orbiter Extended Study - Final Report Prepared for Jet Propulsion Laboratory m California Institute of Technology Sponsored by the National Aeronautics and Space Administration under Contract NAS7-918 'r, s 4 Prepared by RCA Government Systemb Division Astro•Electronics Princeton, New Jersey Authors K. Clark, A. Placco, ^^ 3,{ P. Kaskiewicz, and ti ` K. Lebsock 1 k4Sgs„1P^i^ Q Contract No. 956291, Modification No, 1 l May 27, 1983 i 0 6 -- RCA Astro-Electronics Excess Science Accommodation Capabilities and Excess Performance Capabilities Assessment for Mars Geoscience and Climatology Orbiter Extended Study - Final Report Prepared for Jet Propulsion Laboratory California Institute of Technology Sponsored by the National Aeronautics and Space Administration under Contract NAS7-918 Prepared by RCA Government Systems Division Astro-Electronics Princeton, New Jersey Authors s K. Clark, A. Flacco, .° P. Kaskiewicz, and R K. Lebsock { t h Contract No. 956291, Modification No. 1 t . , May 27, 1983 ^i r ^ i R0/1 Astro-Electronics ABSTRACT This report contains an assessment of the excess science accommodation and excess performance capabilities of a candidate spacecraft bus for the MGCO mission. The appendices are included to support the conclu- sions obtained during this contract extension. The appendices address r the mission analysis, the attitude determination and control,. the r propulsion subsystem, and the spacecraft configuration. t • 1 LO •. 1^ ti44kST:1.iF;t." r it TABLE OF CONTENTS i Section Pag e I. INTRODUCTION I-1 II. CONFIGURATION CONSIDERATIONS II-1 A. General II-1 B. Science Instrument Accommodation II-3 1. Science FOV Instrument Requirements II-3 2. Science Instrument Constraints II-4 a III. SPACECRAFT BUS SUBSYSTEM ASSESSMENT III-1 A. General III-1 B. Spacecraft Bus Excess Capability III-2 1. General III-2 2. Power Subsystem III-2 3. Command Control and Data Handling III-2 4. Attitude Control. Subsystem I11-3 5. Structure III-4 6. Thermal III-4 r 7. Propulsion Subsystem III-4 i ^ IV. SUMMARY AND RECOMMENDATIONS IV-1 APPENDICES A: Fission Analysis A-1 B. Attitude Control System Overview B-1 C. Propulsion Subsystem C-1 D. Configuration Discussion D-1 r z i r N r 11 . 1 } -ss ... ^ gyp - 9A. i • I. INTRODUCTION This contract extension to the basic Mars Orbiter study addresses the identi- fication of "excess capability" beyond the mission/system requirements, "excess capability" for science accommodation, and constraints on the accommodation of science instruments. As this study effort progressed it became apparent that "excess capability" can be defined in a number of ways. It may be defined as (a) capability above the absolute minimum required to meet the mission requirements, or (b) the capabil- ity beyond the normal margins of performance included in an optimized space- craft approach. "Excess capability" in many cases cannot be defined solely by a numerical value (ex; extra instrument mounting space on the nadir facing side of the space- craft, or "excess" instrument weight or power capacity has no meaning if an additional candidate instrument has cooler or viewing field-of-view (FOV) re- quirements that would be incompatible with an existing configuration). Fur- ther, "excess capability" may be available for only certain parts of a mission (as in portions of a power profile) and its utility depends on the use to which that "excess capability" can be put. One of the TIROS series of spacecraft (TIROS-N) has been used as the baseline for the extended study effort. It was selected since it can provide sufficient bus performance for the Mars Orbiter mission. It does provide some excess capability (above the normal margins used on spacecraft designs) in certain subsystems. However, other spacecraft in the TIROS/DMSP series (ATN, SAATN, DMSP Block 5D-3, etc.) can provide significantly more "excess capability" if that is required for margin or growth (see Table 1). The following factors have been kept in mind while performing that extended study. a. Applicability of the approach to the mission requirements b. Meeting payload and launch vehicle interfaces C. Improving reliability d. Consideration of cost factors e. Minimizing complexity f. Flexibility i I-1 0 During the extended study, the tasks that were emphasized, in addition to those of the modified contract requirements, were (a) reiteration of mission analysis, (b) review of the power requirements, (c) updating the instrument interface requirements, (d) detailing the attitude control approach, and (e) reviewing the candidate configurations. These tasks were oriented toward assessing the capabilities of the spacecraft approach against the standard requirements document and the science accommodation factors. A summary of the results of these tasks is shown in the following appendices. Appendix A Mission Analysis Appendix B Attitude Control System Overview Appendix C Propulsion Subsystem Appendix D Configuration Discussion URIGINAL PAGE 19 OF POOR QUAI ITY 1^ W H ^ _ le m'r, G fyl H = 0 ♦ O O ^ 11 ^ o _ ^ . L ^ s, m{^ a N p^p, ^ ^ ^ es ♦ J ^ r N W W^ N N M r IA (^ Z ^ 1A 7 ^ r ^ N^^ ` W ^ ^ ^ N I ^O p W 1 t~ ~__ ` O O Q m J- N t Z H O 0 S E-^ O O ^ 7 O` W a Q w v J 2 ^ ^ o F p aLa. Uoc W aU a. a .n r ^ N W n Ul ui ^- o J = O E-^ w Lo ♦ ^- m 0 v 7 l^ U. c^ v _ J ^p e o -'y1 J F^ (- !^f O f^l O f'18 p ~ ^ J CL cc m Q m > U F^ J y W Q Q O Q a ~ W W W (7 Q ca H ♦ W ^' W ZQ O 0 O Q • • Z > I r. W S N U. N N 2 I A t I-3 r UPIG I NAL PAGC IS OF POOR Q' IN ITY fI 44 T $.- J Q ° >r M u i^ ir m^ U W m O O D U ° < O N O J b r ^ ^ ^ V ^ J Q O 1Lf c^ O 1 _ ° V_ O ~ O y NO @a N W m 0 0 Gr 7 C QN N C J a N G a Y V m Q O J m = y N Ix O x L_ UO 2 N ^`^ r Q Q n Q h 3c Y O .a O Q H W a m 0 a H d N Q N.1 U W O O } O J a V <-) C-1 1 ! _' ° _ o .D^ D V ti O mpg G < L Y O N ; N N E O a N N N E+ _J Q CL 1 ^ _ N X O } 2 (nJ O '^ ° s O m a p= O U H O .D y ^ Q O ^ H f ^ < Y O I .n of F- O w = O H z W H U O 2 (,^ Q oJ N _ } Q 2¢ N Q H Z W W ¢ O 2 0 F W O Z F- Z C, H O = W (^ Q O W W < .D U O(A d W W J< C • • • • d I^ V LU 1 I-4 4. II. CONFIGURATION CONSIDERATIONS A. GENERAL r The proposed complement of science instruments requires modification to the spacecraft configuration shown to JPL in the MGO/LG0 presentation and the Asteroid Rendezvous Spacecraft report. s i, In addition to satisfying science instrument requirements, the spacecraft configuration and attitude in all mission phases must satisfy the requirements for solar array illumination for all phases of the mission as discussed in the Attitude Control section. To assist in this discussion a sketch of the proposed deployed configuration is shown in Figure 1 (see Section D17 for acronyms). The basic spacecraft is the TIROS -N vehicle mentioned earlier. The main body of the spacecraft has 3 circulary 18-inch diameter thermal louvers along its side pane7a. The array is shown in the deployed position. When stowed, it is wrapped around the main body. The .earth facing dish antenna is mounted on the body f E! opposite to the Mars facing instrument panel and is gimballed for earth tracking. In the stowed configuration in the STS during the launch phase, the antenna boom is folded along the peak of the spacecraft body. The extendable and retractable booms for the MAG and GRS are located on the side panels of the spacecraft body. I^ All other instruments are mounted on the liars-facing panel of the spacecraft, allowing for the FOV ' s for date collection and cooling needs.
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