中国空间科学技术

›› 2011, Vol. 31 ›› Issue (3): 62-70.doi: 10.3780/j.issn.1000-758X.2011.03.010

• 技术交流 • 上一篇    下一篇

月地转移轨道快速设计与特性分析

张磊1，于登云2，张熇1   

  1. （1 北京空间飞行器总体设计部，北京 100094)(2 中国航天科技集团公司，北京 100048）
  • 收稿日期:2010-08-09 修回日期:2010-11-19 出版日期:2011-06-25 发布日期:2011-06-25
  • 作者简介:张磊 1981年生，2006年获北京航空航天大学飞行器设计专业硕士学位，现为中国空间技术研究院飞行器设计专业博士研究生。研究方向为轨道设计。

Preliminary Design and Characteristic Analysis of Moon-to-Earth Transfer Trajectories

ZHANG  Lei1, YU  Deng-Yun2, ZHANG  He1   

  1. (1 Beijing Institute of Spacecraft System Engineering, Beijing 100094)(2 China Aerospace Science and Technology Corporation, Beijing 100048)
  • Received:2010-08-09 Revised:2010-11-19 Online:2011-06-25 Published:2011-06-25

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摘要： 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。

关键词: 采样返回, 轨道设计, 月地转移轨道, 大气再入, 月球探测器

Abstract: With the constraints of atmosphere reentry interface parameters and the landingpoint 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, ascentdescent 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.

Key words: Sampling return, Orbit design, Moon-to-earth transfer trajectory, Atmospheric entry, Lunar probe