Abstract
An analytical approach is developed for determining the spacecraft attitude response for stick-slip induced disturbances of a large extended structure with tension control mechanism (TCM). In this method, attitude dynamics with flexible appendage is formulated as a general constrained mode model, and coupling with the stick-slip induced oscillations is formulated as the transition of equilibrium states of modal parameters. Numerical calculations are presented for the flexible solar array on the Advanced Earth Observing Satellite (ADEOS), which caused unexpected attitude oscillations due to the stick slip on the orbit.
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