论文部分内容阅读
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 special situation of orbital maneuver of non-cooperative target satellites in space rendezvous, the orbit controller design method of tracking satellites is studied. Taking into account the uncertainty of parameters and the actuator saturation characteristics, an approximate model of the orbital relative orbital motion is established under the inertial system. The target orbital maneuver is considered as the system disturbance and the tracking satellite control interference is considered, and the fuel consumption and time are optimized The controller design goals based on the limited system performance and the L2-L∞ gain of the system are proposed. The sufficient conditions for the existence of the controller are proposed and proved by using the linear inequality technique, and the controller design problem is transformed into a convex optimization problem. The simulation results show that the designed controller is effective and robust to the uncertainties and disturbances.