As the desire to push space exploration grows, new and more sophisticated space crafts will have to be developed. During the preliminary design phase, a particularly difficult task is determining the optimal placement of the different avionic components in a space vehicle cabin. This problem is a multi-disciplinary, multi-objective optimization problem that can take the form of several different functions including minimizing the wiring between the components, keeping the thermal and electrical loading of all panels within required limits, and/or keeping the mass imbalance within prescribed limits. Traditionally, this task is done manually by a team of systems engineers based heavily on their personal experience. Unfortunately, as the number of avionic components increases, the highly iterative process becomes incredibly time consuming and will most likely lead to a sub-optimal baseline layout. The purpose of this thesis is to outline the creation of an optimization code that can be used as a pre-CAD tool for a systems engineer during the preliminary design phase. The primary focus of this tool is the minimization of space vehicle cable mass while constrained by the size of the attitude control system. Through the research, this thesis has verified a methodology that takes into account multiple types of avionic components as well volumetric interference during the configuration optimization. This tool could greatly improve efficacy and lead to better configuration.
|Commitee:||Shankar, Praveen, Torabzadeh, Jalal|
|School:||California State University, Long Beach|
|Department:||Mechanical and Aerospace Engineering|
|School Location:||United States -- California|
|Source:||MAI 81/3(E), Masters Abstracts International|
|Subjects:||Aerospace engineering, Engineering|
|Keywords:||Aerospace engineering, Avionic components, Cable weight, Layout optimization, Simulated annealing, Space vehicle|
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