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Please use this identifier to cite or link to this item: http://hdl.handle.net/1807/17501

Title: Spacecraft Thermal Design Optimization
Authors: Chari, Navin
Advisor: Damaren, Christopher John
Department: Aerospace Science and Engineering
Keywords: Spacecraft Design
Thermal Optimization
0756
Issue Date: 7-Aug-2009
Abstract: Spacecraft thermal design is an inverse problem that requires one to determine the choice of surface properties that yield a desired temperature distribution within a satellite. The current techniques for spacecraft thermal design are very much in the frame of trial and error. The goal of this work is to move away from that procedure, and have the thermal design solely dependent on heat transfer parameters. It will be shown that the only relevant parameters to attain this are ones which pertain to radiation. In particular, these parameters are absorptivity and emissivity. We intend to utilize an optimal/analytical approach, and obtain a solution via optimization. As mentioned in the motivation, having a purely passive thermal system will greatly reduce costs, and our optimization solution will enable that. This topic involves heat transfer (conduction and radiation), spacecraft thermal network models, numerical optimization, and materials selection.
URI: http://hdl.handle.net/1807/17501
Appears in Collections:Master
Institute for Aerospace Studies - Master theses

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