Fuel optimal low thrust rendezvous with outer planets via gravity assist  

作　　者：GUO TieDing JIANG FangHua BAOYIN HeXi LI JunFeng 

机构地区：[1]School of Aerospace, Tsinghua University, Beijing 100084, China

出　　处：《Science China(Physics,Mechanics & Astronomy)》2011年第4期756-769,共14页中国科学：物理学、力学、天文学（英文版）

基　　金：supported by the National Natural Science Foundation of China(Grant Nos. 10832004 and 11072122)

摘　　要：Low thrust propulsion and gravity assist (GA) are among the most promising techniques for deep space explorations.In this paper the two techniques are combined and treated comprehensively,both on modeling and numerical techniques.Fuel optimal orbit rendezvous via multiple GA is first formulated as optimal guidance with multiple interior constraints and then the optimal necessary conditions,various transversality conditions and stationary conditions are derived by Pontryagin's Maximum Principle (PMP).Finally the initial orbit rendezvous problem is transformed into a multiple point boundary value problem (MPBVP).Homotopic technique combined with random searching globally and Particle Swarm Optimization (PSO),is adopted to handle the numerical difficulty in solving the above MPBVP by single shooting method.Two scenarios in the end show the merits of the present approach.Low thrust propulsion and gravity assist （GA） are among the most promising techniques for deep space explorations. In this paper the two techniques are combined and treated comprehensively, both on modeling and numerical techniques. Fuel optimal orbit rendezvous via multiple GA is first formulated as optimal guidance with multiple interior constraints and then the optimal necessary conditions, various transversality conditions and stationary conditions are derived by Pontryagin＇s Maximum Princi- ple （PMP）. Finally the initial orbit rendezvous problem is transformed into a multiple point boundary value problem （MPBVP）. Homotopic technique combined with random searching globally and Particle Swarm Optimization （PSO）, is adopted to handle the numerical difficulty in solving the above MPBVP by single shooting method. Two scenarios in the end show the merits of the present approach.

关 键 词：low thrust fuel optimal trajectory maximum principle homotopic technique gravity assist 

分 类 号：O242.23[理学—计算数学] V412.41[理学—数学]