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文中确定了一个切换函数和控制律,设计了一个针对近圆轨道无扰动理想状态下航天器相对运动的滑模控制器,使实际状态与期望状态偏差达到或接近于0。切换函数和控制律的稳定性的证明利用了Lyapunov函数。最后通过Matlab仿真实验验证了该滑模控制器的有效性。
In this paper, a switching function and control law are defined, and a sliding mode controller is designed for spacecraft relative motion without disturbance in a nearly circular orbit so that the deviation between the actual state and the expected state reaches or approaches zero. Proof of the stability of switching functions and control laws makes use of the Lyapunov function. Finally, the effectiveness of the sliding mode controller is verified by Matlab simulation.