摘要
针对空间交会中非合作目标卫星存在轨道机动的特殊情况,研究了追踪卫星的轨道控制器设计方法。考虑参数的不确定性和执行器饱和特性,在惯性系下建立了两星相对轨道运动的近似模型;将目标卫星轨道机动视作系统干扰并考虑追踪卫星控制干扰,以燃料消耗和时间为优化指标,提出了基于系统有限时间性能和系统L2-L∞增益的控制器设计目标;采用线性不等式技术提出并证明了控制器存在的充分条件,并将控制器设计问题转化为凸优化问题求解。仿真结果表明,设计的控制器有效且对不确定性和干扰具有较好的鲁棒性。
Aiming at the orbit maneuver of the non-cooperative target satellite.The orbit control method of chasing spacecraft for rendezvous is researched in this paper.Firstly,an approximate model of relative orbit is built in inertial system by considering parametric uncertainty and saturation actuators.Secondly,the orbit maneuver of the target satellite is treated as system disturbance.Regarding the fuel consumption and time as optimization index,the controller design target is given,which is based on the system L2-L∞ gain and finite-time performance.Then,the sufficient conditions of controller are derived,which are based on linear matrix inequalities,and the controller design is transformed into a convex optimization problem.The simulation results show that the controller is effective with good robustness.
出处
《航天控制》
CSCD
北大核心
2014年第3期51-56,61,共7页
Aerospace Control
