Aiming at the conflict of the stationary and rapidness of the terminal mode switching when the variable speed control moment gyro is applied as the actuator on the agile remote sensing satellite for attitude maneuver

on the basis of considering the frame speed error

the attitude error parameter is designed as the switching index

the transition rule within the error parameter switching area is formulated

and the command torque is assigned to CMG and flywheel in real time and solved respectively. A control torque gyroscope/reaction flywheel fuzzy smooth switching control law is proposed. In order to make the attitude of the satellite at the end of attitude maneuver reach the requirements of attitude stability and pointing accuracy in a shorter time

the clustering variation improved particle swarm optimization algorithm is proposed to optimize the parameters of the control law and determine the best switching region and switching parameters. Finally

the simulation results show that the improved particle swarm optimization algorithm always shows better fitness than the traditional particle swarm optimization algorithm in the same iteration times

with faster convergence speed and higher convergence accuracy. Compared with the existing control law

the fuzzy smooth switching control law after parameter optimization can complete the smooth switching of dual modes in a shorter time. At the end of attitude maneuver

the requirements of attitude stability and pointing accuracy can be reached more quickly

and the control performance of agile maneuver and high stable pointing of remote sensing satellites can be improved

which raises the quality of imaging mission.