Free return orbit design and characteristics analysis for manned lunar mission  

作　　者：PENG QiBo SHEN HongXin LI HaiYang 

机构地区：[1]College of Aerospace and Material Engineering, National Univ. of Defense Technology, Changsha 410073, China

出　　处：《Science China(Technological Sciences)》2011年第12期3243-3250,共8页中国科学（技术科学英文版）

基　　金：supported by the National Natural Science Foundation of China (Grant No.10902121)

摘　　要：A circumlunar free return orbit design model that satisfies manned lunar mission constraints is established. By combining analytical method with numerical method,a serial orbit design strategy from initial value design to precision solution is proposed. A simulation example is given,and the conclusion indicates that the method has excellent convergence performance and precision. According to a great deal of simulation results solved by the method,the free return orbit characters such as accessible moon orbit parameters,return orbit parameters,transfer delta velocity,etc. are analyzed,which can supply references to constitute manned lunar mission orbit scheme.

关 键 词：manned lunar mission free return orbit orbit design orbit characters 

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] V4-09