Multi-objective interplanetary trajectory optimization combining low-thrust propulsion and gravity-assist maneuvers

作     者：SHEN HongXin ZHOU JianPing PENG QiBo LI HaiYang LI JiuTian 

作者机构：College of Aerospace and Material EngineeringNational University of Defense TechnologyChangsha 410073China 

出 版 物：《Science China(Technological Sciences)》 (中国科学（技术科学英文版）)

年 卷 期：2012年第55卷第3期

页      面：841-847页

核心收录：

学科分类：12[管理学] 1201[管理学-管理科学与工程(可授管理学、工学学位)] 07[理学] 080202[工学-机械电子工程] 08[工学] 0804[工学-仪器科学与技术] 070105[理学-运筹学与控制论] 0802[工学-机械工程] 0701[理学-数学] 

基　　金：supported by the Open Research Foundation of Science and Technology on Aerospace Flight Dynamics Laboratory of China (Grant No. 2012afdl005) 

主　　题：trajectory optimization low thrust gravity assist multiple objective mission differential evolution 

摘      要：To expand mission capabilities needed without a proportional increase in cost or risk for exploration of the solar system,the multiple objective trajectory using low-thrust propulsion and gravity-assist technique is ***,low-thrust,gravity-assist trajectories pose significant optimization challenges because of their large design ***,the planets are selected as primal scientific mission goals,while the asteroids are selected as secondary scientific mission goals,and a global trajectory optimization problem is introduced and *** multi-objective decision making process is transformed into a bi-level programming problem,where the targets like planets with small subsamples but high weight are optimized in up level,and targets like asteroids with large subsamples but low weight are optimized in down ***,the selected solutions for bi-level programming are optimized thanks to a cooperative Differential Evolution(DE) algorithm that is developed from the original DE algorithm;in addition,an sequential quadratic programming(SQP) method is used in low-thrust *** solution approach is successfully applied to the simulation case of the multi-objective trajectory design *** results obtained are presented and discussed.