航天器降维姿态-轨道一体化控制算法  

Dimension Reduction Attitude and Orbit Integrated Control Algorithm of Spacecraft

作　　者：张恒浩[1] 刘岱[1] 唐庆博[1] 郑正路[1] 张霞[1] Zhang Heng-hao;Liu Dai;Tang Qing-bo;Zheng Zheng-lu;Zhang Xia(R&D Center,China Academy of Launch Vehicle Technology,Beijing,100076)

机构地区：[1]中国运载火箭技术研究院研究发展中心

出　　处：《导弹与航天运载技术》2019年第5期91-96,共6页Missiles and Space Vehicles

基　　金：国家预研项目基金(513201102)

摘　　要：针对航天器控制系统在本体坐标系下出现单轴姿态控制失效的问题,提出一种降维姿态-轨道一体化控制算法。该首先设计降维姿态稳定控制器,通过对其他两轴的姿态控制实现对航天器全姿态的渐近稳定控制;然后设计耦合轨道控制器,引入自适应滑模控制器,在单轴失效情况下确保轨道控制的渐近稳定,最后给出降维姿态稳定控制器和耦合轨道控制器渐近稳定控制的证明过程。仿真结果表明,提出的降维姿态-轨道一体化控制算法可将单轴控制失效的航天器调整到渐近稳定控制状态,计算结果满足工程精度要求。Aiming at the problem that the single axis attitude control is invalid when the spacecraft is working in the primitive coordinate system, an integrated control algorithm with dimension reduction attitude and orbit is designed. Firstly the algorithm designs a dimension reduction attitude controller which uses other two axis’ attitude control to carry out spacecraft’s all-attitude asymptotic stability control. Then it designs the coupled orbit controller and uses adaptive sliding controller to make sure the orbit asymptotic stability control when the single axis attitude control is invalid. At last the proving process with dimension reduction attitude stability controller and coupled orbit controller is provided. Simulation results demonstrate that the algorithm can control the spacecraft whose single axis attitude control is invalid to adjust asymptotic stability. The result can satisfy the engineering precision.

关 键 词：自适应控制 渐近稳定 降维 姿态稳定 滑模控制 

分 类 号：V448[航空宇航科学与技术—飞行器设计]