小行星探测多脉冲交会轨道多目标优化  

Multi-objective Optimization of Multi-impulse Rendezvous Trajectory for Exploring Asteroids

作　　者：李九天[1] 罗亚中[1] 唐国金[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《国防科技大学学报》2011年第3期5-9,共5页Journal of National University of Defense Technology

基　　金：国家自然科学基金资助项目(10902121);国防科技大学科研计划项目(JC09-01-01)

摘　　要：现有的小行星探测交会轨道研究多集中于二脉冲最优燃料研究,本文则研究了小行星探测多脉冲交会轨道多目标优化问题。基于Lambert交会算法建立了包含地球逃逸轨道和日心转移轨道的多脉冲交会轨道优化模型,以燃料消耗最小和转移时间最短为两个优化目标函数。采用一类典型的多目标进化算法———NSGA-Ⅱ用于Pareto最优解的确定。求解了2个小行星探测任务用于验证模型与方法的有效性。结果表明本文方法可以快捷有效地揭示小行星探测任务的出发时刻、转移时间和燃料消耗等特征参数之间的关系,分析不同脉冲数目对最优轨道的影响,以及评价对比不同小行星探测的任务特征。所提出方法在小行星探测任务概念设计中具有较好的应用价值。The current studies on optimal rendezvous trajectories for exploring asteroids always concentrate on the fuel-optimal two- impulse rendezvous, while the aim of this paper is aimed to investigate the multi-objective optimization problem of multiple-impulse rendezvous for exploring asteroids. A multiple-impulse rendezvous optimization model using l.ambert algorithm for exploring asteroids including earth departure and heliocentric transfer phases was established, which utilized minimum-fuel cost and minimum-time transfer as two objective functions. The NSGA-II algorithm, a very representative multi-objective evolutionary algorithm, was employed to obtain the Pareto solution set. The effectiveness of the proposed optimization model and algorithm was testified by solving two asteroids mission design problems. The results show that the proposed method can effectively and efficiently demonstrate the relations among the mission characteristic parameters such as launch time, transfer time and total fuel cost, and analyze the influences of different impulse numbers, and also compare and evaluate different exploration missions. The propesed method has good application value for preliminary mission design for asteroid exploration.

关 键 词：小行星探测 多脉冲交会 多目标优化 

分 类 号：V11[航空宇航科学与技术—人机与环境工程]