›› 2011, Vol. 31 ›› Issue (1): 8-15.doi: 10.3780/j.issn.1000-758X.2011.01.002

• 研究探讨 • 上一篇    下一篇

精确动力学模型下的火星探测轨道设计

陈杨, 赵国强, 宝音贺西, 李俊峰   

  1. (清华大学航天航空学院,北京 100084)
  • 修回日期:2010-08-16 出版日期:2011-02-25 发布日期:2011-02-25
  • 通讯作者: 陈杨 联系地址:北京清华大学航天航空学院,邮编 100084 E-mail:chenyang@126.com
  • 作者简介:陈 杨 1986年生,2009年毕业于清华大学航天航空学院,现于清华大学攻读飞行器设计专业硕士学位。研究方向为深空探测轨道设计与优化。
  • 基金资助:

    国家自然科学基金(10832004)

Orbit Design for Mars Exploration by the Accurate Dynamic Model

 CHEN  Yang, ZHAO  Guo-Qiang, BAOYin  He-Xi, LI  Jun-Feng   

  1. (School of Aerospace Engineering, Tsinghua University, Beijing 100084)
  • Revised:2010-08-16 Online:2011-02-25 Published:2011-02-25

摘要: 首先在二体意义下采用粒子群优化算法(PSO)求解Lambert问题,确定发射窗口和二体地火转移轨道。使用圆锥曲线拼接法设计地心停泊轨道、逃逸轨道,并作为轨道精确设计的初值,以建立在火星的B平面参数和地火转移时间为约束,在精确动力学模型下进行微分迭代修正,最终得到满足约束的精确轨道。将设计轨道在STK软件中仿真,结果吻合。

关键词: 二体问题, 微分迭代, 轨道设计, 精确动力学模型, 火星探测器, 仿真

Abstract: The precision orbit design for Mars exploration by the accurate dynamic model was studied. The launch window and trans-Mars orbit was determined through the partical swarm optimization (PSO) algorithm within the heliocentric two-body restriction. The patched conics method was introduced to design the earth-centred parking orbit and departure hyperbolic orbit. The solution of two-body Lambert problem was input as initial value for precision orbit design, and the preliminary orbit was corrected with the restrictions of the Mars B-plane parameters and flight time by the accurate dynamic model. Finally the designed orbit was simulated with the STK softwares.

Key words: Two-body problem, Differential iteration, Orbit design, Precision dynamic model, Mars probe, Simulation