基于形状的行星际小推力转移轨道初始设计方法  

A Shape-Based Design Approach to Interplanetary Low-Thrust Transfer Trajectory

作　　者：尚海滨[1] 崔平远[1] 乔栋[1] 

机构地区：[1]北京理工大学深空探测技术研究所,北京100081

出　　处：《宇航学报》2010年第6期1569-1574,共6页Journal of Astronautics

基　　金：国家自然科学基金(10832004)资助项目;高等学校博士学科点专项科研基金(20091101120003);北京理工大学基础研究基金(20090142012)

摘　　要：初始设计问题是行星际小推力转移轨道设计中的难点。本文在对逆多项式逼近方法进行改进基础上,提出一种星际小推力转移轨道初始设计方法。首先,通过分析逆多项式逼近轨道的动力学特性,推导了关键系数的可行取值范围;然后,基于改进的逆多项式逼近理论,通过对加速度约束进行处理,建立了一种简单有效的星际小推力轨道设计模型;最后,为高效可靠的获得最优设计参数,采用微分进化算法对轨道设计模型进行了寻优计算。该方法不仅避免了传统逆多项式逼近遗漏可行轨道的缺陷,并且设计参数少,能够为精确设计提供一组可靠的初始设计参数。仿真计算验证了该方法的有效性。Primary design is a challengeable task in research of interplanetary low-thrust transfer trajectory.In this paper,a robust design approach to interplanetary low-thrust transfer trajectory is presented by modifying a traditional inverse polynomial theory in the paper.Firstly,by analyzing the dynamics characteristics of the inverse polynomial-based trajectory,the feasible searching bound for key coefficients is derived.Secondly,through dealing with the acceleration constraint,a simple design model is established based the modified inverse polynomial theory.Finally,in order to obtain the optimal design parameters effectively and reliably,a differential evolution algorithm is used to optimize the design model.The proposed approach has a few design parameters and could avoid the disadvantage of missing the feasible trajectory.Furthermore,it could provide a reliable initial guess for accurate design.The validity of the algorithm has been validated by numerical simulation.

关 键 词：小推力 转移轨道 初始设计 逆多项式 微分进化 

分 类 号：V41[航空宇航科学与技术—航空宇航推进理论与工程]