近地轨道航天器编队构形重构的一种四冲量控制方法

A Four-impulses Control Method for Reconfiguration of LEO Spacecraft Formation Flying

研究近地轨道航天器编队构形重构的一种多冲量控制技术。首先,基于Hill动力学方程研究轨道坐标系中三种推力器安装模式的能控性,发现在沿迹向与轨道面法向安装推力器的简单模式具有对相对运动的完全能控性;其次,将航天器编队构形重构问题划分为简单问题和复杂问题两类,并用始末构形的振幅与相位参数来表达;基于相对运动的叠加性,提出了实现构形重构的四冲量控制方法,并给出根据始末构形参数求解控制冲量大小和施加时刻的解析式;最后,进行仿真,对控制效果的偏差量进行了数值分析,并提出了一种修正沿迹漂移的二冲量方法。仿真结果表明:四冲量控制是一种有效的构形重构底层控制方法,具有简单、实用、低耗、能准确预估燃耗、适合于航天器编队的自主运行以及能显著降低复杂编队构形重构问题难度等诸多优点。

A multi-impulses control technique for reconfiguration of low earth orbit(LEO) spacecraft formation flying(SFF) is studied.Firstly,based on the Hill's equations,the controllability of three different layout modes of thrusters in local vertical and local horizontal(LVLH) reference frame are studied,which show that the mode of thrusters only in in-track and cross-track directions has full controllability to relative motions.Then,the reconfiguration problem of LEO SFF is classed as the simple reconfiguration a...