CAJ | 학술논문

针对我国嫦娥二号卫星拓展任务需求，研究了卫星由日地 L2点向 L 1点的转移轨道方案。基于卫星真实星历，考虑各种摄动因素，借助不变流形理论和微分修正方法，设计了嫦娥二号在日地平动点 L 1和 L2之间的转移轨道，提出了便于理解和工程应用的平动点间直接转移方式，研究了真实力模型下平动点 Lissajous轨道的不变流形转移方式，对比了两种转移方式的出发速度增量、转移时间与出发时刻的关系。研究表明，嫦娥二号可以通过直接转移方式或者借助不变流形进入日地 L 1点 Lissajous 轨道，直接转移方式下有42天出发机会，基于不变流形方式下最短转移时间为210天，对应速度增量5．776 m/s，最小速度增量可达0．024 m/s。研究结果可直接应用于我国嫦娥二号拓展任务的轨道设计与控制，并为我国后续平动点等深空探测任务提供有益借鉴。
침대아국항아이호위성탁전임무수구，연구료위성유일지 L2점향 L 1점적전이궤도방안。기우위성진실성력，고필각충섭동인소，차조불변류형이론화미분수정방법，설계료항아이호재일지평동점 L 1화 L2지간적전이궤도，제출료편우리해화공정응용적평동점간직접전이방식，연구료진실력모형하평동점 Lissajous궤도적불변류형전이방식，대비료량충전이방식적출발속도증량、전이시간여출발시각적관계。연구표명，항아이호가이통과직접전이방식혹자차조불변류형진입일지 L 1점 Lissajous 궤도，직접전이방식하유42천출발궤회，기우불변류형방식하최단전이시간위210천，대응속도증량5．776 m/s，최소속도증량가체0．024 m/s。연구결과가직접응용우아국항아이호탁전임무적궤도설계여공제，병위아국후속평동점등심공탐측임무제공유익차감。
The CHANG’E-2 transfer trajectory scheme from the Sun-Earth L 2 point to the L 1 point is stud-ied to meet the needs of CHANG’E-2 extended missions.Based on the current CHANG’E-2 Lissajous trajec-tory and considering real perturbation,the CHANG’E-2 transfer trajectory from L 2 to L 1 is designed by using invariant manifold and differential correction.The transfer trajectory has two ways including the sim-ple direct delta-v transfer and the one based on invariant manifold.The first way is simple and easy for engi-neering application.The second way focuses on the invariant manifold of Lissajous orbit under real perturba-tion.For these two ways,the relation of delta-v and transfer time with departing time is specially investiga-ted.The results show that CHANG’E-2 can enter the L 1 Lissajous trajectory by the two ways and the direct way has a departing chance of 42 days.Additionally,the manifold way has the shortest transfer time of 2 1 0 days with a delta-v of 5 .7 7 6 m/s and the least delta-v of 0 .024 m/s.The research can be applied directly to the trajectory design and control of CHANG’E-2 extended missions and to our future libration point mission and deep space exploration.