载人登月绕月自由返回轨道与窗口精确快速设计  

Rapid Design of Circumlunar Free-Return High Accuracy Trajectory and Trans-Lunar Window for Manned Lunar Landing Mission

作　　者：贺波勇[1] 李海阳[1] 周建平 

机构地区：[1]国防科学技术大学航天科学与工程学院,长沙410073 [2]中国载人航天工程办公室,北京100720

出　　处：《宇航学报》2016年第5期512-518,共7页Journal of Astronautics

基　　金：国家自然科学基金(11372345;11402295);国家重点基础研究发展计划(973计划)(2013CB733100)

摘　　要：针对载人登月任务背景及工程约束,提出一种轨道与窗口一体化设计方法。通过两次坐标转化,将自由返回轨道设计参数解耦为近月点独立变量。在双二体假设下,通过4段二体轨道拼接完成自由返回轨道初值快速搜索及匹配近地停泊轨道(LEO)面的月窗口,其结果作为下一步采用序列二次规划(SQP)迭代求解高精度动力学模型轨道参数的初值,在该条精确轨道近月点时刻90 min邻域内产生可以匹配LEO地月转移入轨相位的零窗口轨道。算例表明,该流程能够精确快速地完成具有复杂任务背景及苛刻工程要求的载人登月绕月自由返回轨道与窗口设计问题。A method for manned lunar landing mission trajectory and trans-lunar window integrated design is proposed considering with the task background and project constraints. Through the two coordinate rotations, circumlunar free-return trajectory parameter is decoupled to the independent variables in perilune. Free-return trajectories parameters and window quick search algorithm matching with low earth orbit （ LEO ） plane are achieved based on 4 stage two-body patched-conic approach under the double two-body model, and the result can be treated as the initial iterative value in the next step, which a free-return trajectory with high precise orbit dynamic model is obtained by sequential quadratic programming （SQP）, a free-return trajectory and zero-window approach to LEO phase are gotten from the generation of the 90min neighborhood trajectories. The design example demonstrates the precision and rapidity of the circumlunar free-return trajectory and trans-lunar window approach with complex task background and rigorous project constraints for manned lunar landing mission.

关 键 词：载人登月 绕月自由返回 轨道设计 停泊轨道匹配 入轨窗口 

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]