基于相对轨道根数的卫星编队重构控制研究

Research on Satellite Formation Reconfiguration Control Based on Relative Orbit Elements

针对卫星编队的重构控制问题，利用相对轨道根数描述编队构形，结合高斯摄动方程并利用始末编队构形的振幅和相位，设计了沿航迹三次冲量控制和侧向一次控制的方法，实现了卫星编队的重构控制；最后进行了数值仿真，并分析了沿航迹漂移的修正方法。仿真结果验证了控制策略的简单性和有效性。

The reconfiguration control problem of formation flying satellites is discussed in this paper. Firstly, the formation configuration is described based on the relative orbit elements. Secondly, based on the Gauss perturbation equation, by using the magnitude and the phase parameters of the initial and the desired formation, the method of three-impulses in the along-track direction and one-im- pulse in the cross-track direction are designed, and the purpose of formation reconfiguration is achieved. In the end, a numerical simulation example is provided and the method of amending the drift of the formation in the along-track direction is analyzed. The simplicity and effectiveness of the given control strategy is verified by the simulation results.