Staring imaging attitude tracking control of agile small satellite

Attitude tracking control during staring imaging of agile small satellite configured with double-gimbaled control moment gyroscope (DGCMG) is investigated. Firstly, considering the characteristics of agile satellites and the mission requirement of staring imaging, design the actuators configuration. Then, using the orbit information to computer the attitude and attitude angular velocity of staring imaging target relative to the satellite body reference frame, and considering avoidance the singularity of CMG to design control law and steering law. Finally, setup the agile small satellite attitude and orbit control simulation system, the mathematical simulation shows that the solution is simple and effective for staring imaging attitude maneuver control of agile small satellites, and conclude that the minimum angular rate of gimbals of DGCMG is the most important factor to determinate the attitude tracking precision.