Time efficient controller design for spacecraft attitude maneuver based on gauss pseudospectral method

The problem of time efficient large angle maneuvers for a rigid spacecraft is researched and addressed in the presence of inertia uncertainty and external disturbances. A real time closed loop optimal control based on pseudospectral method is utilized to fullfill the mission. First, with the help of Gauss pseudospectral method, the optimal control problem is converted to nonlinear programming problem, and the time optimal solution, that is, the desired path to guide the spacecraft, is derived. Second, adaptive synergetic control is adopted to design the attitude tracking controller. Simulation results prove the robust and time efficient properties of the derives controller.