东篱科研大数据发现系统（DRDS）

位置：成果数据库 > 期刊 > 期刊详情页

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

ISSN号：0567-7718
期刊名称：《力学学报：英文版》
时间：0
分类：V11[航空宇航科学与技术—人机与环境工程] P541[天文地球—构造地质学;天文地球—地质学]
作者机构：[1]School of Aerospace Engineering,Beijing Institute of Technology,100081 Beijing, China, [2]Key Laboratory of Dynamics and Control of Flight Vehicle,Ministry of Education,100081 Beijing, China
相关基金：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

作者： Ya-Min Wang[1,2] Dong Qiao[1,2] Ping-Yuan Cui[1,2]

关键词：月球轨道, 地球表面, 能量转移, 小行星, 太阳, 系统, 设计, 差分进化算法, Lunar orbit, Asteroid exploration, Low-energy transfer, Sun-Earth-Moon system

中文摘要：

从一条月亮的轨道的开始在这被调查的星状的探索轨道工作。探查离开月亮的轨道并且回到土的附近，这被假定，然后，由执行一个近地点的地球的逃跑调遣。在 Sun-Earth-Moon 系统的低精力的转移被采用。首先，到在在在 Sun-Earth-Moon 系统的地球表面上面的 5 000km 高度以内的近地点的从月亮的轨道的低精力的转移的可行区域计算、分析。三种转移类型被发现，即，大演习和快转移，小演习和快转移，和混乱、慢的转移。大多数可行性轨道属于开始的二种类型。然后，到近地点的从月亮的轨道的低精力的轨道腿和到流星的从近地点的一条以太阳为中心的轨道腿被近地点演习修正。最佳的完整转移的轨道被利用微分进化算法获得。最后，作为目标拿 4179 Toutatis 流星，一些低精力的转移轨道被获得并且分析。

英文摘要：

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.

同期刊论文项目