Design of low-energy transfer from lunar orbit to asteroid in the Sun-Earth-Moon system  

作　　者：Ya-Min Wang Dong Qiao Ping-Yuan Cui 

机构地区：[1]School of Aerospace Engineering,Beijing Institute of Technology [2]Key Laboratory of Dynamics and Control of Flight Vehicle,Ministry of Education

出　　处：《Acta Mechanica Sinica》2014年第6期966-972,共7页力学学报（英文版）

基　　金：supported by the National Basic Research Programof China(973 Program)(2012CB720000);the National Natural Science Foundation of China(11102020);Program for New Century Excellent Talents in University;Beijing Higher Education Young Elite Teacher Project and China Scholarship Council

摘　　要：Asteroid exploration trajectories which start from a lunar orbit are investigated in this work.It is assumed that the probe departs from lunar orbit and returns to the vicinity of Earth,then escapes from the Earth by performing a perigee maneuver.A low-energy transfer in Sun-EarthMoon system is adopted.First,the feasible region of lowenergy transfer from lunar orbit to perigee within 5 000 km height above the Earth surface in Sun-Earth-Moon system is calculated and analyzed.Three transfer types are found,i.e.,large maneuver and fast transfers,small maneuver and fast transfers,and disordered and slow transfers.Most of feasibility trajectories belong to the first two types.Then,the lowenergy trajectory leg from lunar orbit to perigee and a heliocentric trajectory leg from perigee to asteroid are patched by a perigee maneuver.The optimal full-transfer trajectory is obtained by exploiting the differential evolution algorithm.Finally,taking 4179 Toutatis asteroid as the target,some low-energy transfer trajectories are obtained and analyzed.Asteroid exploration trajectories which start from a lunar orbit are investigated in this work.It is assumed that the probe departs from lunar orbit and returns to the vicinity of Earth,then escapes from the Earth by performing a perigee maneuver.A low-energy transfer in Sun-EarthMoon system is adopted.First,the feasible region of lowenergy transfer from lunar orbit to perigee within 5 000 km height above the Earth surface in Sun-Earth-Moon system is calculated and analyzed.Three transfer types are found,i.e.,large maneuver and fast transfers,small maneuver and fast transfers,and disordered and slow transfers.Most of feasibility trajectories belong to the first two types.Then,the lowenergy trajectory leg from lunar orbit to perigee and a heliocentric trajectory leg from perigee to asteroid are patched by a perigee maneuver.The optimal full-transfer trajectory is obtained by exploiting the differential evolution algorithm.Finally,taking 4179 Toutatis asteroid as the target,some low-energy transfer trajectories are obtained and analyzed.

关 键 词：Lunar orbit Asteroid exploration Low-energy transfer Sun-Earth-Moon system 

分 类 号：P185.7[天文地球—天文学] P173