基于多圆锥曲线法的着陆器奔月轨道设计与特性分析

针对载人登月任务中人货分运飞行模式，精确快速设计了着陆器(LM)的奔月轨道，分析了轨道窗口特性。以着陆器的奔月出发时刻、纬度幅角和加速脉冲为设计变量，基于多圆锥曲线法动力学模型，利用序列二次规划（SQP）优化算法对奔月轨道快速求解。在地心白道系下提出了近月点伪经度判别准则，该方法可为轨道设计参数初值提供正确参考。最后以伪倾角为窗口特性分析参数，发现了近月点窗口、近地点出发位置的变化规律。仿真结果表明，本文提出的伪经度搜索方法能够快速求解着陆器地月转移轨道，同时揭示了环月到达轨道(LLO)与近地出发轨道(LEO)之间的内在联系，研究结论可为未来载人登月工程提供借鉴。

Design and Characteristic Analysis for Lunar Module’s Trans Lunar Trajectory Based on Multi Conic Method

On the principle of splitting the crew and cargo in a manned lunar mission, an accurate and fast approach is proposed to design the lunar module (LM) trans-lunar trajectory and to analyze the trans-lunar window’s characteristics. Firstly, based on the multi-conic method, the departure time, the argument of latitude and the acceleration impulse are chosen as the variables with the sequential quadratic programming (SQP) algorithm to calculate out the trans-lunar trajectory. Then in the Earth-centered Earth-to-Moon plane, the perilune-longitude principle is presented which could provide the appropriate initial value of the design variables. Lastly, from the characteristic analysis of the pseudo inclination, the change rule of the perilune window duration and the departure position is found. The simulation results demonstrate that the perilune-longitude principle is effective to calculate out the trans-lunar trajectory and help reveal the relationship between the low Earth orbit (LEO) and the low lunar orbit (LLO). The study’s conclusions could supply references to China’s manned lunar landing mission in the future.