›› 2011, Vol. 31 ›› Issue (3): 26-34.doi: 10.3780/j.issn.1000-758X.2011.03.005

• 研究探讨 • 上一篇    下一篇

目标飞行器交会对接轨道的设计和控制

李革非1,2, 宋军2, 谢剑锋2, 韩潮1, 许尤福2   

  1. (1 北京航空航天大学宇航学院,北京 100083)(2 北京航天飞行控制中心航天飞行动力学技术重点实验室,北京 100094)
  • 收稿日期:2010-11-04 修回日期:2010-12-27 出版日期:2011-06-25 发布日期:2011-06-25
  • 作者简介:李革非 1966年生,2001年获北京航空航天大学航天工程专业硕士学位,研究员,现为北京航空航天大学在职博士,研究方向为航天器轨道力学与轨道控制,从事载人航天和深空探测轨道控制工作。
  • 基金资助:

    国家自然科学基金(41005020)

Rendezvous Orbit Design and Control of the Target Spacecraft

 LI  Ge-Fei1,2, SONG  Jun2, XIE  Jian-Feng2, HAN  Chao1, XU  You-Fu2   

  1. (1 Beihang University, Beijing 100083)(2 Beijing Aerospace Control Center,Science and Technology on Aerospace Flight Dynamics Laboratory, Beijing 100094)
  • Received:2010-11-04 Revised:2010-12-27 Online:2011-06-25 Published:2011-06-25

摘要: 根据目标飞行器轨道高度和追踪飞行器入轨轨道高度,给出了目标飞行器交会对接轨道初始相位的设计方法。针对目标飞行器交会对接轨道控制要求,建立了共面相位计算模型以及轨道相位、高度和圆化度的多目标参数求解模型。基于定轨误差、轨道控制误差和轨道预报误差的调相时间分析,制定了目标飞行器调相控制策略。仿真计算表明,实现的目标飞行器交会对接轨道满足要求,验证了调相控制量优化原则的正确性,并对标称共面与虚拟共面的共面时刻和共面相位进行了比较。所提出的计算模型、控制策略和分析方法适用于目标飞行器交会对接轨道设计和控制实施。

关键词: 交会, 对接, 轨道控制, 目标飞行器

Abstract: According to the target spacecraft′s orbit height and the chaser spacecraft′s orbit height, the design method of the target′s initial phase for the rendezvous orbit was presented. The mathematical models of the target′s rendezvous orbit control were established, which included the model of the coplanar phase and the model of the multi objective parameters to solve the target′s orbit phase, height and eccentricity. Based on the target′s phasing time analysis of orbit determination error, orbit control error and orbit prediction error, the strategy of the target′s phasing orbit maneuver was developed. Simulation results indicate that the target′s rendezvous orbit is obtained to meet the requirements of the objective orbit and the optimization principles of phasing control delta velocity is verified. Even the difference of the normal coplanar and the virtual coplanar is compared. The proposed model, control strategy and analysis methods are applicable to the target′s rendezvous orbit design and control implementation.

Key words: Rendezvous, Docking, Orbit control, Target spacecraft