基于相对轨道要素的卫星编队构型重构制导算法

Guidance Algorithm for Satellite Formation Reconfiguration Based on Relative Orbit Elements

针对卫星编队飞行过程中由于任务的改变或成员的进出导致编队构型重构的问题,推导和定义了描述卫星编队的相对轨道要素;提出了基于相对轨道要素的卫星编队构型重构制导算法;使用该算法对近地圆轨道上的卫星编队重构过程中各控制因素与速度增量的关系进行了分析。结果表明,该算法能够综合考虑构型重构时运行状态、约束条件、调整策略、能量消耗等因素,便于实现编队重构的整体优化。

In the full paper, we explain our guidance algorithm in detail. In this abstract, we just add some pertinent remarks to listing the three topics of explanation. The first topic is. relative orbit elements. In topic one, we review briefly those contents of the conference paper by Lovell et al that are useful to us in developing our guidance algorithm. The second topic is. the guidance algorithm for satellite formation reconfiguration based on relative orbit elements. Topic two adopts two-thrust control model to compute the incremental velocity △V. The third topic is. numerical simulation example and the analysis of simulation results. Topic three considers three different situations： （1） with reconfiguration transfer angle fixed at 10°, 30°, 50°, 70° or 90°, the variation of △V with transfer time; （2） the variation of △V with transfer angle under certain conditions; （3） with relative trajectory radius fixed at 100, 200, 300,400 or 500 m, the variation of △V with transfer angle. The simulation results for these three situations are given respectively in three figures in the full paper. The simulation results indicate preliminarily that our algorithm can take into account the flying state, the restricting conditions, the transfer program, and the impulse requirements simultaneously and satisfactorily.