Abstract:

The large angle attitude maneuver control of spacecraft with bounded inputs is investigated. To remove the singularity due to the use of Euler angle in large angle attitude maneuver, the kinematics of the spacecraft is described by quaternion. Using Lyapunov theory, and motivated by the recent results on invariant set stability theorems of nonlinear impulsive hybrid systems, a class of large angle attitude maneuver hybrid dynamical controller with bounded inputs is derived. Theoretical analysis and simulation results indicate that the proposed control algorithm has excellent dynamic performance and can be easily designed and realized.

Key words: experimental technology of aerocraft, attitude control, large angle attitude maneuver, Lyapunov approach, bounded inputs, quaternion