The problem of attitude recovery of flexible spacecraft is investigated using the feedback linearization control approach. The attitude and flexible dynamics equations for a class of spacecrafts are presented. The resulting nonlinear and coupled dynamic equations and the corresponding nonlinear control algorithms of the system are implemented into a high-fidelity, user-friendly simulation environment The simulator is used for both analysis and design investigation of attitude recovery of spacecraft using the feedback linearization approach numerical results for a representative case are included to demonstrate the capabilities of the proposed control and modeling methodologies.
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