Optimal periodic controller for formation flying on libration point orbits
Optimal periodic controller for formation flying on libration point orbits
复制标题
平动点轨道编队飞行最优周期控制器
DOI：
10.1016/j.actaastro.2011.04.020
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发表时间：
2011-09-01
影响因子：
3.5
通讯作者：
Zhong, Wanxie
中科院分区：
文献类型：
--
作者：
Peng, Haijun;Zhao, Jun;Zhong, Wanxie
针对航天器沿着日地系统周期平动点轨道的位置保持和编队保持稳定任务，提出了一种基于连续小推力的最优周期控制器。此外，提出了一种新的数值算法求解周期Riccati微分方程的最优周期控制器的设计。实际飞行任务表明，利用相对动力学模型的线性周期时变方程设计的最优周期控制器克服了时变LQR控制器存在的问题和局限性。在此基础上，对一个领头航天器位置保持和三个跟随航天器编队保持任务进行了非线性数值仿真。数值仿真表明，航天器控制速度增量和相对位置误差随轨道高度的变化不大。此外，在地球轨道偏心性质和初始注入误差的扰动下，引导航天器和跟随航天器的实际轨道以高精度跟踪周期参考轨道。特别是，由最优周期控制器获得的航天器编队相对位置误差都在毫米级。(C)2011爱思唯尔有限公司保留所有权利。
An optimal periodic controller based on continuous low-thrust is proposed for the stabilization missions of spacecraft station-keeping and formation-keeping along periodic Libration point orbits of the Sun-Earth system. Additionally, a new numerical algorithm is proposed for solving the periodic Riccati differential equation in the design of the optimal periodic controller. Practical missions show that the optimal periodic controller (which is designed with the linear periodic time-varying equation of the relative dynamical model) overcomes the problems and limitations of the time-variant LQR controller. Furthermore, nonlinear numerical simulations are presented for the missions of a leader spacecraft station-keeping and three follower spacecraft formation-keeping. Numerical simulations show that the velocity increments for spacecraft control and relative position errors vary little with changes in the altitude of periodic orbits. In addition, the actual trajectories of the leader and the follower spacecraft track the periodic reference orbit with high accuracy under the perturbation of the eccentric nature of the Earth's orbit and the initial injection errors. In particular, the relative position errors obtained by the optimal periodic controller for spacecraft formation-keeping are all in the range of millimeters. (C) 2011 Elsevier Ltd. All rights reserved.