人工平动点附近混合推进航天器编队滑模控制保持  

Sliding mode control for formation flying near libration points using hybrid propulsion

作　　者：贺京九 袁长清[2] 龚胜平 赵磊 HE Jingjiu;YUAN Changqing;GONG Shengping;ZHAO Lei(School of Aviation Operations and Services,Air Force Aviation University,Changchun 130011,China;School of Aviation Fundamentals,Air Force Aviation University,Changchun 130011,China;School of Astronautics,Beihang University,Beijing 100191,China)

机构地区：[1]空军航空大学航空作战勤务学院,长春130011 [2]空军航空大学航空基础学院,长春130011 [3]北京航空航天大学宇航学院,北京100191

出　　处：《北京航空航天大学学报》2023年第5期1222-1230,共9页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：针对近距离航天器编队在日地系人工L1点附近的飞行控制问题,提出一种将太阳帆推进技术与库仑力编队技术相结合的混合推进控制方法。通过控制从航天器太阳帆相对于主航天器的姿态角调整主从间光压力差,同时与主从间库仑力相配合,既解决仅依靠太阳帆控制而存在的欠驱动问题,又改善了库仑编队的可控性。以太阳帆圆形限制性三体问题(SSCRTBP)模型为基础,给出共线人工平动点位置的计算方法,并构造主航天器运行轨道;引入航天器间库仑力,推导出混合推进编队相对运动方程;设计了固定时间滑模控制策略,以从航天器太阳帆的2个姿态角和主从间电荷积为控制量,对编队构型进行控制,将其与LQR控制策略对比,仿真结果表明:固定时间滑模控制策略在控制精度、所需时间、能量消耗等方面均优于LQR控制策略。在时长3年的任务中,编队仅用23天就展开完毕,保持阶段基线相对误差小于1%,其他两轴误差在厘米量级,整个过程无工质消耗,对于今后开展长期深空探测任务具有重要意义。Aiming at the flight control problem of proximity spacecraft formation near the artificial L1point of the sun-earth system,a hybrid propulsion control method combining solar sail propulsion and Coulomb force formation technology is proposed.By controlling the relative attitude angles of the follower’s sail,the solar radiation pressure difference between two spacecraft can be adjusted,and matched with Coulomb force,not only the underactuated problem of solar sail control alone is solved,but the controllability of Coulomb formation is also improved.Firstly,based on the solar sail circular restricted three-body problem(SSCRTBP)model,the calculation method of the position of the collinear artificial libration point is given and the orbit of the main craft is constructed.The relative motion equation of the hybrid propulsion configuration is then determined by the introduction of the Coulomb force between spacecraft.Finally,the fixed-time sliding mode control strategy is designed to control the formation configuration by taking the two attitude angles of the follower’s sail and the charge product between the two crafts as the control parameters.Then the sliding mode control strategy is compared with the LQR control strategy in order to reflect its high performance.The simulation results show that the fixed-time sliding mode control strategy is superior to the LQR control strategy in terms of control accuracy,required time and energy consumption.During a 3-year mission,the formation can be deployed in only 23 days.The baseline relative error is less than 1%,whereas the error on the other two axes is on the scale of centimeters.For long-term deep space exploration trips in the future,the fact that no fuel is used throughout the entire process is extremely important.

关 键 词：平动点编队 太阳帆推进 库仑力编队 混合推进 滑模控制 LQR控制 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]