Attitude recovery of flexible spacecraft using nonlinear control

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.