Study on Control Technology of Attitude for Micro-Satellite Via Reaction-Wheel

Based on spacecraft attitude dynamics equation,control algorithm for micro-satellite of three-axis stabilization via reaction-wheel was studied.With improved PD control algorithm,in which anticipant target angle and angle rate function was served as input,the acceleration of reaction-wheel was served as output,effective control for micro-satellite was realized,in which decouple-operation to the dynamics equation was avoided.The results showed that the method issued was effective in repressing disturbance and not sensitive to system error,which had high steady accuracy(1×10-4 rad).The method was simple and efficient,which is convenient for computer on the satellite to disposal in application.