Abstract: To deal with spacecraft three axis large attitude maneuver with the external disturbances and actuator uncertainties, a new adaptive output feedback controller was presented based on the extended state observer. Firstly, an attitude dynamic model by the Momentum theorem and Euler method was established. Secondly, based on the fact that the extended state observer could minimize the nonlinear coupling and external disturbances, the adaptive output feedback control strategy was developed only with the attitude angle output, which could compensate the control toque error during the large angle attitude maneuver. Finally, simulation results show that the precise attitude maneuver can be accomplished and the angles can converge to the desired states for different cases.

Key words: Extended state observer, Adaptive controlOutput feedback, Attitude maneuver, Nonlinear system, Spacecraft