中国空间科学技术2013，Vol.33Issue(2)：25-31,40,8.DOI:10.3780/j.issn.1000-758X.2013.02.005
基于间接法的最优小推力逃逸轨道设计
Indirect Optimization of Low Thrust Escape Trajectories
黄镐 1韩潮1
作者信息
- 1. 北京航空航天大学宇航学院,北京100191
- 折叠
摘要
Abstract
At present,most of the research on low thrust escape trajectory optimization were limited to planar escape or unconstrained engine model.Using the indirect method,the unknown parameters of the two-point-boundary-value-problem were bounded in a hyper unit sphere by multiplying a positive unknown parameter to the fuel optimal performance index.Firstly,the two-dimensional short-time fuel-optimal escape trajectory without control constraint was solved by the homotopy method and curve fits technology.Finally,the three-dimensional long-time fuel-optimal escape trajectory with control constraint was solved.This method is validated to be high-accuracy,good-convergence and efficient for low thrust escape trajectory optimization.关键词
小推力/逃逸轨道/燃料最优/星际探测Key words
Low thrust/Escape trajectory/Fuel optimization/Interplanetary exploration引用本文复制引用
黄镐,韩潮..基于间接法的最优小推力逃逸轨道设计[J].中国空间科学技术,2013,33(2):25-31,40,8.
