偏心航天器有限推力姿轨耦合控制  

Integrated Orbit and Attitude Control of Spacecraft with Deviated Centroid and Finite Thrust

作　　者：刘江[1] 贾英宏[1] LIU Jiang;JIA Yinghong(Beijing University of Aeronautics and Astronautics,Beijing 102206,China)

机构地区：[1]北京航空航天大学,北京102206

出　　处：《空间控制技术与应用》2024年第4期45-54,共10页Aerospace Control and Application

基　　金：国家自然科学基金资助项目(11772023)。

摘　　要：针对偏心航天器存在大轨控推力偏心以及轨控推力大小不可调节的问题,提出一种有限推力轨道与姿态控制方案.该轨道控制方案可以同时控制多个轨道要素.轨道控制中将控制量设计为推力角,解决轨控推力大小不可调节的问题.设计姿态控制方案对轨控所期望的推力角进行跟踪,并考虑轨控推力偏心形成的大干扰力矩.针对大干扰问题对传统的渐近稳定姿态控制律进行了改进,从而利用三轴姿态的耦合关系抵消干扰力矩的影响.通过数值仿真验证了轨道姿态控制方案的有效性.A finite thrust orbit and attitude control scheme is proposed to solve the problem of unadjustable orbit control thrust with large misalignment for a spacecraft with deviated centroid.The proposed orbit control scheme can control multiple orbit elements at the same time.The problem of unadjustable orbit control thrust is solved by taking the thrust angle as the control input of orbit control.When designing the attitude control strategy to track the de-sired attitude of orbit control,the large interference torque caused by the thrust misalignment is considered.To solve the problem of large disturbance,the traditional asymptotically stable attitude control law is improved.The coupling relationship of three-axis attitude is used to counteract the influence of interference torque.The effective-ness of the orbit and attitude control strategy is verified by numerical simulation.

关 键 词：姿轨耦合 有限推力 推力偏心 姿态跟踪 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]