航天器Halo轨道间转移的滚动时域控制  

Receding Horizon Control of the Spacecraft for Transferring between Halo Orbits

作　　者：彭海军[1] 谭述君[2] 吴志刚[1,2] 

机构地区：[1]大连理工大学工业装备结构分析国家重点实验室,大连116024 [2]大连理工大学航空航天学院,大连116024

出　　处：《宇航学报》2012年第8期1027-1034,共8页Journal of Astronautics

基　　金：国家自然科学基金(11102031;11002032;11072044);中央高校基本科研业务费资助(DUT11ZD(G)02)

摘　　要：针对航天器在日/地系统共线平动点附近Halo轨道族之间的轨道转移问题,提出了一种在线实时求解滚动时域控制的新方法。首先采用高效的辛自适应非线性最优控制数值算法,离线规划出航天器在不同Halo轨道之间转移的最优轨迹和最优控制输入。然后提出一种在线实时求解滚动时域控制的新方法,基于已规划好的最优转移轨迹,应用滚动时域控制方法完成航天器在初始入轨偏差下的在线实时制导控制任务。最后的非线性动力学系统数值仿真结果表明:所提出的求解滚动时域控制的方法具有高效率特点,能够在线实时求解航天器在Halo轨道之间转移的制导控制问题,并很快消除初始入轨误差的影响。A new method is presented for solving the on-line receding horizon control problem in real time, and it has been successfully applied into the transfer mission between the Halo orbits near collinear Libration points in the Sun-Earth system. First, by employing the efficient symplectic adaptive algorithm for nonlinear optimal control, the optimal transfer trajectory and control input are programmed off-line. Then, a new on-line real time numerical algorithm is proposed for solving the receding horizon control. Based on the optimal transfer trajectory and control, the transfer mission of the spacecraft with initial injection error is accomplished by using the receding horizon control method. Finally, the receding horizon controller is implemented for the transfer mission between Halo orbits. Finally numerical simulation results for nonlinear dynamics system show that the numerical method proposed for receding horizon control is effective, and it can solve the transfer mission between Halo orbits in real time. Beside, the initial injection error can be removed quickly.

关 键 词：平动点 HALO轨道 轨道转移 轨迹优化 滚动时域控制 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]