Optimized design of controller parameters for large angle spacecraft attitude maneuvers

An optimized large angle attitude controller was designed for rapid spacecraft maneuvers based on a Lyapunov controller model of a quaternion. The design parameters are given for the optimized variables and the optimal time is given for the optimized objectives, with the output moment as the constrain condition. A hybrid genetic algorithm is used to solve for the optimized controller parameters. Simulations show that optimized controller effectively shortens the maneuver time, bound by the output moment constraint. This simple, effective method does not rely on the designer's experience.