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Abstract
A relatively general formulation for studying the dynamics of spacecraft with interconnected flexible bodies is presented accounting for thermal deformations and transverse vibrations of the structural members. In addition, the shift in the center of mass of the system and the slewing maneuvers of the members are incorporated. The formulation can be applied to study the U.S. proposed Space Station as well as a large class of present and future spacecraft. An example illustrates application of the formulation. The model under study is a satellite with a central rigid body and a pair of appendages. The satellite response is investigated numerically over a range of system parameters and effect of the thermal deformations assessed. An approximate closed-form (analytical) solution of the problem is also obtained to quickly assess trends and gain better physical appreciation of response characteristics.
Published Version
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