Variable structure control of small satellite for large angle maneuver

Large angle maneuver is one of the critical techniques for high resolution telemetry small satellites. Reaction wheels are usually used as the executor of attitude maneuver for stabilizing satellite attitude. A step by step optimization based on the maximum theory and the variable structure control theory are suggested to make the maneuver time shorter within the limit of reaction wheel's, saturated rate. An approximate optimal controller is designed to overcome the difficulty of direct optimization. Simulation results indicate that the control algorithm has an excellent robustness and can be easily designed and realized.