论文部分内容阅读
为解决航天器编队飞行过程中的故障容错、障碍规避以及碰撞避免等重要的飞行安全问题,提出了一种新颖的自适应轨道控制方法。该方法将人工势函数制导与滑模控制技术相结合,利用一类特殊的人工势函数来描述障碍规避及碰撞避免等要求,并基于此为航天器编队设计了协同控制器,使得编队在实现目标追踪和构型保持的同时,能够避免相互碰撞并具备规避障碍物的能力。更为重要的是,控制器中自适应律的引入使得闭环系统对执行机构故障、外界干扰及参数不确定性具备良好的容错能力,显著增强了闭环系统的鲁棒性。最后,典型的仿真分析验证了所提控制方法的有效性。
In order to solve the important flight safety problems such as fault tolerance, obstacle avoidance and collision avoidance during the spacecraft formation flight, a novel adaptive orbit control method is proposed. This method combines artificial potential function guidance and sliding mode control technology, and uses a special class of artificial potential functions to describe the requirements of obstacle avoidance and collision avoidance. Based on this, a coordinated controller is designed for spacecraft formation to make formation Target tracking and configuration maintenance, while avoiding collisions and have the ability to avoid obstacles. More importantly, the introduction of adaptive law in the controller makes the closed-loop system have a good fault-tolerant ability to actuator failure, external disturbance and parameter uncertainty, and significantly enhances the robustness of the closed-loop system. Finally, the typical simulation analysis verifies the effectiveness of the proposed control method.