基于弹道逃逸和小推力捕获的地月转移轨道设计  

Design of trans-lunar trajectory based on ballistic escape and low-thrust capture

作　　者：彭坤[1] 黄震[1] 杨宏[1] 张柏楠[1] PENG Kun;HUANG Zhen;YANG Hong;ZHANG Bainan(Institute of Manned Space System Engineering,China Academy of Space Technology,Beijing 100094,China)

机构地区：[1]中国空间技术研究院载人航天总体部,北京100094

出　　处：《航空学报》2018年第8期227-237,共11页Acta Aeronautica et Astronautica Sinica

基　　金：载人航天预先研究项目(010201)~~

摘　　要：针对地月空间货运任务和环月轨道空间设施建设任务,提出一种弹道逃逸和小推力捕获相结合的新型地月轨道转移模式,并建立了一整套该类型轨道设计方法。首先,在三体模型假设下分别建立地心弹道逃逸轨道和月心小推力捕获轨道的二维极坐标动力学模型。对于弹道逃逸轨道,将地心旋转系对准角和地月转移加速速度增量作为控制变量,提出初值估计解析公式,并应用序列二次规划算法进行快速求解。对于小推力捕获轨道,以月心距为参考量设置与弹道逃逸轨道的拼接点约束,提出能量匹配方法预估飞行时间,采用最优螺旋轨道的初始伴随状态解析式预估近月点伴随变量初值。基于混合法和轨道逆推思想,采用人工免疫算法进行小推力捕获轨道求解。仿真结果表明,基于弹道逃逸和小推力捕获的地月轨道转移方式大幅降低了近月制动燃料消耗,能快速穿越地球辐射带,且飞行时间适中;同时,提出的轨道设计方法能快速搜索到基于弹道逃逸和小推力捕获的地月转移轨道,验证了该方法的有效性。Considering the mission of cargo delivery in the cislunar space and the mission of space facility construction in the circumlunar orbit,a new Earth-Moon orbit transfer mode based on ballistic escape and low-thrust capture is proposed,and a complete set of design method for this type of trajectory is established.First,the two-dimensional polar coordinate dynamics models for the geocentric ballistic escape trajectory and the selenocentric low-thrust capture trajectory are established respectively based on the hypothesis of three-body model.For the ballistic escape trajectory,the alignment angle in the geocentric rotating frame and the velocity increment of trans-lunar injection are selected as control variables,analytic formulas for initial value estimation are proposed,and the sequential quadratic programming algorithm is applied to quickly search this trajectory.For the low-thrust capture trajectory,selenocentric distance is considered as reference quantity to set the splicing point constraints with ballistic escape trajectory,an energy matching method is proposed to estimate the flight time,and the initial values of adjoint variables in perilune are estimated by using analytic formulas of initial adjoint states for optimal spiral trajectory.Based on the hybrid method and backward orbit propagate,the artificial immune algorithm is used to solve the low-thrust capture trajectory.Simulation results show that the Earth-Moon orbit transfer based on ballistic escape and lowthrust capture can significantly reduce fuel consumption of lunar orbit insertion,and can fly through the radiation belts of Earth quickly with moderate flight time.The trajectory design method proposed in this paper can rapidly search the trans-lunar trajectory with ballistic escape and low-thrust capture,validating the effectiveness of this method.

关 键 词：地月转移轨道 地月空间 双脉冲转移 小推力 人工免疫算法 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]