Design and optimization of low-energy transfer orbit to Mars with multi-body environment  

作　　者：LU Yi LI HengNian LI JiSheng CHE Zheng YANG YiKang YANG Yuan SUN Yang 

机构地区：[1]School of Electronic and Information Engineering, Xi’an Jiaotong University [2]State Key Laboratory of Astronautic Dynamics (ADL), Affiliated to Xi’an Satellite Control Center [3]College of Aeronautics and Astronautics, University of Electronic Science and Technology of China [4]School of Aerospace, Xi’an Jiaotong University

出　　处：《Science China(Technological Sciences)》2015年第10期1660-1671,共12页中国科学（技术科学英文版）

基　　金：supported by the National Hi-Tech Research and Development Program of China("863"Project)(Grant No.2010AA7040014)

摘　　要：This paper discusses the problem of design and optimization of low-energy transfer orbit with multi-body environment. A new integrative method is proposed to effectively solve the problem, in which the parameterized patched manifolds in CR3BP(circular restricted three-body problems), the shape-based method with multi-body environment, the homotopic method with multi-body environment, and the low-thrust capturing and descending algorithm with multi-body environment are all included. Firstly, the parameters describing the patched manifolds in CR3 BP are optimized until the least total absolute velocity increment has been got, including the employment of the shape-based method with multi-body environment. Secondly, the low-thrust control laws of the transfer orbit are optimized employing the homotopic method with multi-body environment that transfers the fuel optimization problem to an easier energy optimization problem. Thirdly, the low-thrust descending orbit around Mars is computed using the laws proposed in this paper. As a typical example, the Earth-Mars transfer orbit design is discussed. The results showed that the parameters describing the patched manifolds could be optimized by the DE(differential evolution) algorithm effectively; the homotopic method with multi-body environment could get the optimal value that meets the first order optimality conditions; and the low-thrust descending orbit could effectively be captured by Mars and finally become a circular parking orbit around it by the hypothesis control laws proposed in this paper. It shows that the final fuel cost is much less than the optimal transfer in the patched two-body problems. In conclusion, the method proposed in this paper could effectively solve the low-energy low-thrust optimal control problem in multi-body environment for the future deep space explorations.

关 键 词：orbit optimization multi-body patched manifolds LOW-ENERGY LOW-THRUST 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程]