载人登月自由返回轨道与Hybrid轨道设计方法  

Free-return Trajectory and Hybrid Trajectory Design for Manned Lunar Landing Missions

作　　者：白玉铸[1] 陈小前[1] 李京浩[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《国防科技大学学报》2010年第2期33-39,共7页Journal of National University of Defense Technology

摘　　要：对自由返回轨道与Hybrid轨道的设计方法进行了研究。应用分段受摄的高精度动力学模型,设计了搜索变量、约束条件与微分修正搜索算法,搜索得到了自由返回轨道标称轨道,并使用STK软件对其进行了验证与三维仿真,最后对误差传递情况进行了分析。Hybrid轨道由自由返回与非自由返回轨道组合而成,文中给出了一条典型的Hybrid轨道设计过程,并对其优缺点进行了简要分析。文章所述方法与结论可应用于载人登月任务轨道设计,也可应用于嫦娥后期工程和搭载发射的微型月球探测器的轨道设计。The method to design lunar flee-return trajectory and hybrid trajectory was studied. The sectional perturbational high precision dynamical model was established, then the search variables, target parameters and differential correction algorithm were designed, and a nominal free-return trajectory was searched out, which was validated and three-dimensionally simulated by STK. In addition, the error transfer was analyzed. The paper described a typical design procedure of hybrid trajectory which combines free-retttm trajectory and non-freereturn trajectory, and simply analyzed the advantages and disadvantages of it. The method and conclusions in the paper can be applied to conceptual design of manned lunar landing mission and trajectory design of the later stage of China hmar Exploration Program, as well as trajectory design of micro lunar probe launched together with other spacecrafts.

关 键 词：自由返回轨道 Hybrid轨道 载人登月 嫦娥工程 微分修正算法 

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]