多冲量轨道交会问题算法研究  

Research on Algorithm of Multi-impulse Orbit Rendezvous Problem

作　　者：曾光[1] 王露莎 李栋林[1] ZENG Guang;WANG Lusha;LI Donglin(Xi’an Satellite Control Center,Xi’an 710043,China)

机构地区：[1]西安卫星测控中心,西安710043

出　　处：《航天器工程》2021年第1期23-30,共8页Spacecraft Engineering

摘　　要：针对平面内轨道交会问题给出了一种多冲量轨道控制算法,其融合了半长轴、偏心率、近地点幅角联合控制方法和轨道相位捕获控制方法。首先建立了等点火时长计算模型和理论起控时刻计算模型,在此基础上设计了控制序列自动调整算法。基于该算法,在给定测控条件、单次控制最大点火时长等约束条件下,可快速求解实现与目标航天器轨道交会的多冲量控制策略。最后,通过轨道交会问题算例,验证了算法的有效性。该方法可应用于轨迹捕获、航天器组网控制、航天器交会远程导引等航天场景。In this paper,a multi-impulse orbit control algorithm is proposed for the in-plane orbital rendezvous problem.The algorithm combines the joint control method of semi-major axis,eccentricity,and argument of perigee and orbit phase capture control method.Firstly,the model of equal control duration and theoretical starting time are established,and then the automatic adjustment algorithm of control sequence is designed.Base on the algorithm,the multi-impulse control strategy for realizing the rendezvous with the target spacecraft orbit can be quickly solved under the constraints of spacecraft tracking,telemetry and control(TT&C)and maximum control duration.Finally,the effectiveness of the algorithm is verified by an example of orbital rendezvous.The method can be applied to aerospace scenes such as trajectory capture,spacecraft network control,and spacecraft rendezvous remote guidance.

关 键 词：轨道交会 多冲量 联合控制 相位捕获 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]