月地转移轨道快速设计与特性分析

摘要

With the constraints of atmosphere reentry interface parameters and the landingpoint location, a method was proposed for the preliminary design of the moon-to-earth trajectory with direct atmosphere reentry. The method included two stages of iteration loops. The inner loop made moon-center orbit and earth-center orbit continuous at the boundary of the moon influence sphere. To solve the earth-center orbit parameters meeting the reentry angle constrain, a method combined Lambert problem and Newton-Raphson method was adopted. The outer loop made the moon-to-earth trajectory meet the landing-point location constrain by adjusting the launch time.The analysis shows that four types of moon-to-earth trajectories meet atmosphere reentry interface parameters. The four trajectories are descent-descent trajectory, descent-ascent trjectory, ascentdescent trajectory and ascent-ascent trajectory. Then the characteristics of the transfer trajectories were analyzed, such as the perigee geocentric distance, the transfer orbit insertion point distribution, the reentry point distribution. Simulation results indicate that the preliminary design method is effective.%对采用直接大气再入方式的月地转移轨道,考虑大气再入界面参数和地面落点位置约束,提出了一种基于双二体模型的快速设计方法.该方法分为内外两层迭代循环,内层循环使月心段轨道和地心段轨道在月球影响球边界处连续,并采用Lambert问题与Newton-Raphson法相集合的方法求解满足再入角约束的地心段轨道参数;外层循环通过调整地心段轨道倾角和轨道置入时间使月地转移轨道满足地面落点位置约束.分析表明,存在四种类型的月地转移轨道满足大气再入界面约束,分别为降-降型、降-升型、升-降型和升-升型.在此基础上,对四种类型月地转移轨道的近地点地心距、置入分布点、再入点分布等特性进行了分析.仿真结果验证了所提出方法的有效性.