Abstract
The thermal-structural performance of deployable appendages can have a significant effect on satellite attitude dynamics and control. Thermally-induced structural motions of appendages such as booms and solar arrays give rise to torques reacting on the main body of a satellite which may result in attitude disturbances. This research considers the behavior of rigid panel solar arrays that utilize a relatively stiff honeycomb sandwich panel construction. The thermal-structural performance of these appendages is investigated through analytical and experimental studies. An analytical model for the transient thermal-structural response of a rigid panel solar array subject to rapid changes in thermal loading is presented. This thermal-structural model is incorporated into a coupled dynamic formulation for the planar dynamics of a simple satellite consisting of a rigid hub and a flexible appendage. Finally, an experimental investigation of the thermal-structural behavior of an actual satellite solar panel is described.
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