The optimal control problem of the attitude of a spacecraft during the stretching process of its solar array was discussed.The equations of motion for the spacecraft with solar array were obtained based on multibody system dynamics.The control problem of the attitude motion of a spacecraft with solar array can be transformed into the motion planning problem of nonholonomic system when the initial angular momentum is zero.The control input of stretching process of solar array on spacecraft was obtained with spline approximation or curve fitting.Particle swarm optimization(PSO) was applied to find the optimal control input.This method solved the problem whose initial and final values are not zero.The results of numerical simulation show that this approach is effective for the control problem of the attitude of a spacecraft during the stretching process of its solar array.
修改评论