摘要
针对在轨服务航天器相对椭圆轨道目标器任务要求,提出了追踪器相对目标器进行绕飞的初始条件及考虑各种摄动情况下轨道保持的最优控制算法。通过对椭圆轨道时变相对线性化方程及解析解的详细分析,给出了追踪器进行绕飞的必要条件。进一步考虑到安全问题,给出了使目标器位于绕飞轨迹中心的条件,同时还进行了给定追踪器形状和距离的绕飞轨迹设计。考虑到实际绕飞中受到各种摄动的影响,结合最优控制理论设计了控制向量受限的离散LQR最优控制器,将追踪器控制在预定的绕飞轨迹中。文中设计了三个控制误差区域,将控制器作用在合理的偏差范围内,避免了因控制测量误差而消耗大量燃料。最后进行了仿真验证,结果表明,文中的设计方法和控制算法合理有效。
Focusing on the requirement of on-orbit-servicing spacecraft to targeter in eccentric orbits, the initial conditions for the chaser flying around the targeter and the optimal control algorithm used to keep the flyaround orbit under perturbance were presented. With detailed analyzing the time variant and relatively linearized formulas and their analytic solutions, the necessary conditions for the chaser flyaround were acquired. To consider the safety, the conditions for the targeter to locate at the center of flyaround orbit and its design under given chaser shape and distance were presented. In view of the influence of perturbance, a discrete LQR optimal controller with constraint control vector to keep the chaser in the scheduled orbit was designed. Three control error boxes enabling the controller to work in the reasonable error areas to avoid fuel wastage for the error measure were also allocated. An example design was validated successfully by a simulation.
出处
《吉林大学学报（工学版）》
EI
CAS
CSCD
北大核心
2006年第3期410-416,共7页
Journal of Jilin University:Engineering and Technology Edition
基金
'973'国家重点基础研究发展规划项目(5131201)
关键词
飞行器设计
在轨服务
轨道设计
最优控制
aerocraft design
on-orbit-servicing
orbit design
optimal control
