中国空间科学技术

中国空间科学技术

• 论文 •    下一篇

基于无线电测量的航天器运动监测方法及验证

陈略1,2,*，路伟涛1，汪筱阳3，张雨佳1，满海钧1，韩松涛1   

  1. 1.北京航天飞行控制中心，北京100094
    2.航天飞行动力学技术重点实验室，北京100094
    3.西安卫星测控中心，西安710043
  • 收稿日期:2024-05-13 修回日期:2024-08-06 录用日期:2024-08-16

Spacecraft movement monitoring method and verification based on radio measurement

CHEN Lue1,2,*, LU Weitao1, WANG Xiaoyang3, ZHANG Yujia1, MAN Haijun1, HAN Songtao1   

  1. 1.Beijing Aerospace Control Center, Beijing 100094， China
    2.National Key Laboratory of Science and Technology on Aerospace Flight Dynamics， Beijing 100094， China
    3.Xi’an Satellite Control Center， Xi’an 710043， China
  • Received:2024-05-13 Revision received:2024-08-06 Accepted:2024-08-16

PDF (PC)

14

摘要： 针对地球高轨及地月空间航天器在轨机动过程中通常下发无线电信号的特点，采用无线电信号被动接收与处理技术，实现对在轨航天器灵敏与快速运动监测。分析了在轨航天器运动监测常用技术手段，提出了基于无线电测量的航天器目标运动被动监测策略方法。首先，基于目标航天器常发下行遥测、数传、载波信号等工况特点，利用无线电接收天线对目标进行跟踪；其次，利用采集与记录设备对目标下行接收信号进行采集与记录；然后，重点阐述通过软件无线电方式对目标下行信号进行处理与分析，精确提取与目标运动关联的信号频率、幅度、相位等变化敏感特征。提出基于开环测量多普勒频率数据的轨控量估计算法，反算评估目标运动状态；最后，对目标运动监测效果进行评估。基于实测试验，实现了地球高轨航天器轨道机动、姿态调整运动过程的准确灵敏监测，精确监测出其轨控起止时间，并估算了其测站视线方向上的轨控量为4.1m/s，推断了该地球高轨航天器采用了小推力连续变轨模式实施轨道机动；实现了月球航天器轨道机动过程信号监测，分别提取出了其频率、幅度、相位特征，并估算了其测站视线方向上的轨控量为0.91m/s。基于无线电测量的航天器运动监测方法，有效弥补了传统雷达、光学测量在航天器运动监测方面的局限性，并与其形成互补。该方法适用于多种新的应用场景，为未来地球高轨与地月空间航天器监测提供了可行的技术方案。

关键词: 航天器, 运动监测, 轨道姿态变化, 无线电测量, 开环测量, 信号处理

Abstract: In terms of the characteristics of radio signals typically emitted by spacecraft in high Earth orbit space and cislunar space during orbital maneuvers, passively receiving and processing techniques for radio signals are employed to achieve sensitive andrapid motion monitoring of spacecraft in orbit. The common technical methods used for spacecraft in orbit motion monitoring are analyzed，and a passive monitoring strategy based on radiometric measurements is proposed. Firstly, based on the operational characteristics of the transmitted telemetry, data transmission, and carrier signals from the target spacecraft, the target spacecraft signal is tracked and received by radio receiving antennas. Secondly, the target spacecraft downlink radio signal is sampled and recorded by the sampling and recording equipment. Subsequently, this paper focuses on the processing and analysis of the target's downlink signals by software-defined radio mode, accurately extracting sensitive features related to the target's motion such as signal frequency, amplitude, and phase changes. The orbit control quantity estimation algorithm based on open-loop Doppler frequency is proposed to evaluate the target's motion state. Finally, the effectiveness of the motion monitoring is assessed. The results indicate that accurate and sensitive monitoring of the orbital maneuvers and attitude adjustment processes of Earth high orbit spacecraft has been achieved based on actual experiment. The starting and ending time of the orbit control is accurately monitored, and the orbit control quantity in the line of sight direction of the station is estimated to be 4.1m/s, suggesting that this Earth high orbit spacecraft adopted a small thrust continuous orbit change mode for orbital maneuvers. The signal monitoring of the lunar spacecraft orbit maneuver process is realized, and its frequency, amplitude and phase characteristics are extracted respectively, and the orbit control quantity in the line of sight direction of the station is estimated to be 0.91m/s. The spacecraft motion monitoring method based on radiometric measurements effectively compensates for the limitations of traditional radar and optical measurements in monitoring spacecraft motion and complements them. This method is suitable for a variety of new application scenarios, and provides a feasible technical solution for the future monitoring of earth high orbit and cislunar space spacecraft.

Key words: spacecraft, motion monitoring, orbit attitude change, radio measurement, open-loop measurement, signal processing