登月飞船两次再入时的基准轨道设计  

Design for Standard Twice Reentry Trajectory of Mooncraft

作　　者：南英[1] 王斯财[1] 

机构地区：[1]南京航空航天大学航天学院,江苏南京210016

出　　处：《上海航天》2010年第5期7-12,27,共7页Aerospace Shanghai

摘　　要：对登月飞船在指定轨道终点及多约束条件下两次再入轨道的优化设计进行了研究。根据多次再入法原理,基于设定的基本参数,给出了轨道设计的流程,仿真计算了二次再入点、弹出点、第一次再入点的参数,以及整体轨道。结果表明该方法可行,可为飞船高速度、多目标约束及高精度落点要求的再入轨道初步设计提供参考。The optimal design of the trajectory for the standard twice reentry of mooncraft under the conditions of the trajectory endpoint set and multiply objective constraints in this paper.The flowchart of the trajectory design was given out based on the general parameters settled according to the principle of the multiply reentry.The parameters of the twice reentry point,rejected point and first reentry point,and the whole trajectory were calculated through the simulation.The results showed that this method was feasible,which could provide a reference for the initial design of the reentry trajectory with high speed,multiply objective constraints and high precision placement.

关 键 词：飞船 再入轨道设计 两次再入轨道 高速 

分 类 号：V412.44[航空宇航科学与技术—航空宇航推进理论与工程]