共轨飞行航天器轨道特性分析  

Analysis of Orbit Characteristics for Co-orbital Spacecraft

作　　者：张相宇 田百义 汪中生[1] ZHANG Xiangyu;TIAN Baiyi;WANG Zhongsheng(Beijing Institute of Spacecraft System Engineering,Beijing 100094,China)

机构地区：[1]北京空间飞行器总体设计部,北京100094

出　　处：《航天器工程》2023年第4期12-20,共9页Spacecraft Engineering

摘　　要：针对与空间站长期共轨飞行的航天器轨道维持问题,文章基于相对轨道参数演化方法,考虑J 2摄动、大气阻力、轨道机动等因素,推导了两航天器升交点赤经、倾角、相位、半长轴等参数间的解析关系,提出了一种共轨飞行的标称轨道设计方法和对应的维持策略,此外,进一步推导了定轨误差、控制误差、环境预报误差和面质比误差对共轨飞行轨道的影响。仿真结果表明:文章提出的解析计算方法与数值仿真结果相比具有较高的精度,给出的维持策略和误差分析方法简化了共轨飞行的轨道设计,在空间站共轨飞行任务中具有重要工程应用价值。In response to the problem of maintaining the orbit of spacecraft in long-term co-orbital flight with the space station,this paper is based on the method of relative orbital parameter evolution,considering the influence such as J2 perturbation,atmospheric drag and maneuver.The relationship between the two spacecraft in right ascension of the ascending node(RAAN),inclination,phase and semi-major axis,etc.is derived analytically.A nominal orbit design method and corresponding maintenance strategy for the co-orbital spacecraft is are proposed.In addition,the influence of co-orbital flying orbit caused by orbit determination error,orbit control error,atmospheric prediction error and area-mass ratio error are derived analytically.The simulation results show that the proposed method in this paper has high precision,the proposed orbital maintenance strategy and error analysis method simplified the design of co-orbital flying orbit and has important engineering application value in space station co-orbital flight mission.

关 键 词：共轨飞行 轨道参数演化 轨道维持 轨道误差分析 

分 类 号：V467[航空宇航科学与技术—航空宇航制造工程]