Elements of Spacecraft Design (2002)(1st ed.)(en)(610s) by Wren Software, Inc. C. Brown

By Wren Software, Inc. C. Brown

This article discusses the conceptual levels of venture layout, structures engineering, and orbital mechanics, delivering a foundation for figuring out the layout method for various elements and features of a spacecraft. insurance comprises propulsion and tool structures, constructions, angle keep watch over, thermal keep an eye on, command and knowledge structures, and telecommunications. labored examples and workouts are integrated, as well as appendices on acronyms and abbreviations and spacecraft layout info. The publication can be utilized for self-study or for a direction in spacecraft layout. Brown directed the workforce that produced the Magellan spacecraft, and has taught spacecraft layout on the college of Colorado.

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Washington. DC. 1979. 7Magel/an Final Report. Vol I. Pre Launch. Manin Marietta. Denver. CO. May 1989. lIWihilden. R. D. c.. HEAO: Case Study in Spacecraft Design. TRW. AIAA. Washington. DC. 1981. q Albaugh. D. H. ). Mars Obsen'er Mission. 'i. Jet Propulsion Lab.. California Inst. of Technology. Pasadena. CA. 1993, IOUnmanned Spa('ecraft Cost Model. S. Air Force Space Division. los Angeles. CA. Aug. 1981. 'i. ANSUAIAAG-020. April 1992. 11Whitting. K.. and Kovalcik. E. S .. AIM Aerospace Design Engineers Guide.

Item 2. the estimate of launch weight, is the difficult issue. 8. 8. These factors are a function of the maturity of the weight item (estimaled. calculated. or actual). and also a function of the equipment type, structure. propulsion. electronics. or cabling. To arrive at a projected launch weight. the sum of all structure mass in the estimated category should be increased by 25%. 6Ck. 6%. The sum of these adjusted masses is the predicted launch mass for structure. The process is repeated for propulsion mass.

Telecommunication is not shown separately: it is included in the CDS mass. The subsystem weights are shown as percentages of spacecraft dry weight. 076 (1868) + 50 = 192 kg 30 4 Propellants required: Calculation of required propellant is discussed an Chapter 4. For now, assume that the propellant required is 1027 kg. On-orbit dry mass: Spacecraft maximum on-orbit dry mass is equal to II 29 LM capability - Adapter - Propellant = 1868 - 192 - 1027 7 7 = 649 kg (1431Ib) 6 6 Allowable subsystem mass: The maximum allowable subsystem or bus mass is equal to On-orbit dry mass - Payload mass load.

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