Close relative motion on distant retrograde orbits  

作　　者：Chihang YANG Ming WANG Hao ZHANG 

机构地区：[1]University of Chinese Academy of Sciences,Beijing 100049,China [2]Key Laboratory of Space Utilization,Technology and Engineering Center for Space Utilization,Chinese Academy of Sciences,Beijing 100094,China

出　　处：《Chinese Journal of Aeronautics》2023年第3期335-356,共22页中国航空学报（英文版）

基　　金：supported by the Strategic Priority Research Program of Chinese Academy of Sciences(No.XDA30010200)。

摘　　要：Distant Retrograde Orbits(DROs)in the Earth-Moon system have great potential to support varieties of missions due to the favorable stability and orbital positions.Thus,the close relative motion on DROs should be analyzed to design formations to assist or extend the DRO missions.However,as the reference DROs are obtained through numerical methods,the close relative motions on DROs are non-analytical,which severely limits the design of relative trajectories.In this paper,a novel approach is proposed to construct the analytical solution of bounded close relative motion on DROs.The linear dynamics of relative motion on DRO is established at first.The preliminary forms of the general solutions are obtained based on the Floquet theory.And the general solutions are classified as different modes depending on their periodic components.A new parameterization is applied to each mode,which allows us to explore the geometries of quasi-periodic modes in detail.In each mode,the solutions are integrated as a uniform expression and their periodic components are expanded as truncated Fourier series.In this way,the analytical bounded relative motion on DRO is obtained.Based on the analytical expression,the characteristics of different modes are comprehensively analyzed.The natural periodic mode is always located on the single side of the target spacecraft on DRO and is appropriate to be the parking orbits of the rendezvous and docking.On the basis of quasi-periodic modes,quasi-elliptical fly-around relative trajectories are designed with the assistance of only two impulses per period.The fly-around formation can support observations to targets on DRO from multiple viewing angles.And the fly-around formation is validated in a more practical ephemeris model.

关 键 词：Distant retrograde orbits Ephemeris model Floquet theory Formation flight Relative motion Spacecraft Three-body problem Transfer singularity 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程]