The invention relates to a segmented optimal attitude tracking control method for a gravity gradient satellite, which aims at a gravity gradient system consisting of a satellite platform, a coiled extension arm and a tail end effective load, adopts a dumbbell model to describe the swinging motion of the gravity gradient system in coplanar orbit transfer, and establishes an attitude dynamic model of the gravity gradient satellite; and an orbit dynamics model is established based on electro-propulsion coplanar orbit transfer. An optimal controller is designed, the segmented optimal trajectory of the gravity gradient satellite under the action of electric thrust is obtained, and the stability and robustness of the system are enhanced while orbit transfer between two coplanar circular orbits is achieved. On the basis, a segmented adaptive terminal sliding mode control method is designed based on a finite time tracking error function, and the problems of finite time convergence and uncertain boundary are solved. The gravity gradient satellite in coplanar orbit transfer serves as a specific object, and the provided control method is beneficial to improvement of control performance and easy to implement.
本发明涉及一种重力梯度卫星分段最优姿态跟踪控制方法,本发明针对卫星平台、盘绕式伸展臂和末端有效载荷三者组成的重力梯度系统,采用哑铃模型来描述其在共面轨道转移中的摆动运动,建立重力梯度卫星的姿态动力学模型;基于电推共面轨道转移建立轨道动力学模型。设计最优控制器,得到电推力作用下重力梯度卫星的分段最优轨迹,在实现两个共面圆轨之间轨道转移的同时,增强系统的稳定性和鲁棒性。在此基础上,基于有限时间跟踪误差函数,设计了一种分段自适应终端滑模控制方法,解决了有限时间收敛和不确定性边界问题。本发明以共面轨道转移中的重力梯度卫星为特定对象,提出的控制方法有利于提升控制性能,易于实现。
Gravity gradient satellite segmented optimal attitude tracking control method
一种重力梯度卫星分段最优姿态跟踪控制方法
2024-07-26
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |