卫星编队飞行的协同控制

Coordinated control of spacecraft formation flying

为了实现卫星编队飞行任务,设计了卫星编队飞行队形协同控制。考虑控制精度以及小推力卫星变轨时间长等特点,采用了相对运动的非线性动力学方程进行数学建模,并采用精度较高的相对轨道根数法设计了目标队形。应用滑模控制理论,设计了跟踪控制器,并通过Lyapunov稳定性理论,证明了控制系统全局渐近稳定性。通过一个“1颗主星与3颗从星”编队的测量基线放大控制仿真,验证了该控制器的可行性。结果表明,该控制器具有控制精度高、实时性强等特点,可用于卫星编队飞行队形协同控制。

This paper considers the problem of coordinated control for earth-orbiting spacecraft formation flying. Because of the long duration of the low-thrust formation maneuvers and the control precision, the analysis includes the nonlinear dynamics of the motion of the follower relative to the leader. A relative element method was used to design the relative formations to generate a natural relative trajectory. A Lyapunowbased design and analysis framework was used to develop a sliding mode controller to guarantee global asymptotic position/velocity tracking errors. A “one leader and three followers” formation baseline enlarging simulation demonstrates the controller performance. The high precision, low computational complexity and good performance of the controller makes it suitable for real-time applications.