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• W2163090356 abstract "THERMAL CONTROL DESIGN ANALYSIS OF AN ON-ORBIT ASSEMBLY SPACECRAFT Richard F. O'Neill Design Specialist General Dynamics Convair Division San Diego, California 92138 Design requirements for large space structures such as the DoD/STS On-Orbit Assembly (OOA) spacecraft include stringent limitations on maximum allowable thermally induced structural deflections. The sheer size of the spacecraft presents some challenging thermal design analysis problems: 1) selection of representative and thermally critical yet manageable analysis regions for thermal-analytical modeling, 2) realistic assessment of energetically pertinent radiation linkage terms in the analysis models, and 3) derivation of local incident space-environmental heat flux histories incorporating complex shadowing effects. These problems were addressed successsfully in the Convair thermal design analysis of the OOA spacecraft by means of a methodical, building-block approach to the task. A brief description is given of the OOA Spacecraft elements. Following development of a rationale for selecting worst-case space environments and spacecraft orientations, space heating analysis methods of the Vector Sweep computer program are summarized. Vector Sweep was employed in computing shadowed incident heat flux histories for subsequent thermal analyses of the OOA Spacecraft structures. Resulting thermal response of typical structural elements is presented. On-Orbit Assembly (OOA) Spacecraft General Dynamics Convair Division has performed a design study of an OOA spacecraft. The study investigated and defined the new technology required to place large, low-density structures on orbit. The technology was applied to the conceptual design of an orbital assembly flight article. Deployment of the DoD/STS OOA Spacecraft module in low earth orbit (LEO) is illustrated in Figure I , which depicts the radial arms, lens array, feedmast, and upper stage hub assembly. The separately deployed feedmast assembly is mated to the module at geosynchronous earth orbit (CEO). Figure 2 shows a typical section of the deployable radial arm. The feedmast configuration is illustrated in Figure 3. The radial arm and feedmast basic structural elements are tubular graphite-epoxy. Over-center lock hinges and thin metal hinges accommodate compact stowage in the Space Transportation System (STS) Orbiter cargo bay. A typical carpenter tape hinge is shown in Figure 4. The radial arms, feedmast, and central hub assembly are major structures requiring definition of on-orbit thermally induced deflections. To this end, thermal design analysis of these structures were performed. Figure 1. On-Orbit Assembly (OOA) Spacecraft Module Deployment CopyrightOAmerican lnbtitute of Aeronautics and Aslronaulics, Inc.. 1979. All rights reserved. 7.5 FT ALL LONGERONS" @default.
• W2163090356 created "2016-06-24" @default.
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• W2163090356 date "1979-05-08" @default.
• W2163090356 modified "2023-10-18" @default.
• W2163090356 title "Thermal control design analysis of an on-orbit assembly spacecraft" @default.
• W2163090356 doi "https://doi.org/10.2514/6.1979-917" @default.
• W2163090356 hasPublicationYear "1979" @default.
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