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基于同波束干涉测量的航天器姿态测量研究

张天刚1,任天鹏2,3,*,谢剑锋2,3,路伟涛2,3,尹飞飞1   

  1. 1北京邮电大学,北京100876
    2北京航天飞行控制中心,北京100094
    3航天飞行动力学技术重点实验室,北京100094
  • 收稿日期:2018-10-31 修回日期:2018-11-27 出版日期:2019-04-25 发布日期:2019-03-19
  • 作者简介:张天刚(1993-),男,硕士研究生,tiangang_zhang@bupteducn,研究方向为干涉测量数据相关处理及相关后处理
  • 基金资助:

    国家自然科学基金(11403001);国家自然科学基金(41604030)

Spacecraft attitude measurement based on samebeam interferometry

ZHANG Tiangang1,REN Tianpeng2,3,*,XIE Jianfeng2,3,LU Weitao2,3,YIN Feifei1   

  1. 1Beijing University of Posts and Telecommunications,Beijing 100876,China
    2Beijing Aerospace Control Center,Beijing 100094, China
    3Science and Technology on Aerospace Flight Dynamics Laboratory,Beijing 100094, China
  • Received:2018-10-31 Revised:2018-11-27 Online:2019-04-25 Published:2019-03-19

摘要: 基于地基同波束干涉测量,建立了航天器姿态测量数学模型及方程,给出了姿态解算方法,并对方程可解性与解算精度因子进行了分析。通过模拟在轨航天器轨道运行,进行了基于同波束干涉测量的航天器姿态解算数值仿真和误差分析,对解算误差和观测俯仰角的关系进行了分析和验证。结果表明,利用3个地面测站针对航天器上3个下行天线信号开展同波束干涉测量,辅以精度因子约束进行姿态解算,可以获得有效的航天器姿态信息,其精度最高可达0.001°。该方法可以作为在轨航天器姿态测量的备份手段。

关键词: 航天器姿态, 地基同波束干涉测量, 姿态测量, 误差分析, 观测俯仰角

Abstract: A samebeam interferometry based mathematical model of spacecraft attitude was established, and a solution method was proposed. The solvability of the model and the precision factor were analyzed. Numerical simulations of spacecraft attitude determination based on samebeam interferometry were carried out, where an onorbit spacecraft was simulated, and the relationship between calculation error and observation pitch angle were analyzed and verified. The results show that the effective spacecraft attitude can be obtained by using three ground stations to carry out the samebeam interferometry for three downlink antenna signals with a constraint of precision factor,and the highest accuracy achieved is 0.001° . The method proposed can be used as an attitude measurement backup for onorbit spacecraft.

Key words: spacecraft attitude, ground samebeam interferometry, attitude measurement, error analysis, observation pitch angle