中国空间科学技术

中国空间科学技术 ›› 2026, Vol. 46 ›› Issue (5): 139-148.doi: 10.16708/j.cnki.1000-758X.2026.0084

• 论文 • 上一篇    下一篇

超精超稳超敏捷航天器参数自主辨识方法

韩明仁1,2，汤亮1,2,*，关新1,2，陈智1,2，宋继良1,2   

  1. 1.北京控制工程研究所，北京100190
    2.空间智能控制技术全国重点实验室，北京100190
  • 收稿日期:2025-09-23 修回日期:2025-10-20 录用日期:2025-10-26 发布日期:2026-09-23 出版日期:2026-09-30

Autonomous identification method for parameters of ultra-high agility, stability and precision spacecraft

HAN Mingren1,2，TANG Liang1,2,*，GUAN Xin1,2，CHEN Zhi1,2，SONG Jiliang1,2   

  1. 1.Beijing Institute of Control Engineering，Beijing 100190，China
    2.Science and Technology on Space Intelligent Control Laboratory，Beijing 100190，China
  • Received:2025-09-23 Revision received:2025-10-20 Accepted:2025-10-26 Online:2026-09-23 Published:2026-09-30

PDF (PC)

21

摘要： 面向超精超稳超敏捷（“三超”）航天器在轨自主运行的需求，针对其结构模态参数辨识问题，提出一种全自主、高精度的在轨辨识方法，以克服传统地面处理方式实时性差、人工干预多的局限。该方法基于作动器扫频数据，通过Savitzky-Golay滤波器实现频响数据降噪，在保留峰值特征的同时显著抑制高频噪声；提出了基于复平面运动速度的峰值检测算法，识别不显著模态；利用导纳圆拟合理论计算各模态频率、阻尼比与增益，并通过分频段最小二乘优化方法全面提升参数估计精度。数值仿真表明，在噪声与扰动下，该方法仍能准确提取模态，优化后频响曲线与理论模型高度一致。最后通过全物理试验验证了其在真实噪声环境中的有效性，有效识别出不显著模态共振峰，最终辨识得到的结构传递函数与实测数据吻合良好，为“三超”航天器高性能自主控制提供了关键技术支撑。

关键词: 参数自主辨识, 超精超稳超敏捷航天器, 模态参数辨识优化, 导纳圆, Savitzky-Golay滤波器

Abstract: In response to the demand for the in-orbit autonomous operation of ultra-high agility, stability, and precision(ASP) spacecraft, this paper proposes a fully autonomous high-precision in-orbit identification method for structural modal parameters. This approach is designed to overcome the limitations of traditional ground-based processing methods which suffer from poor real-time performance and require significant manual intervention. The proposed method utilizes actuator frequency sweep data and employs a Savitzky-Golay filter to denoise the frequency response data, which significantly suppresses high-frequency noise while preserving key peak features. A novel peak detection algorithm, based on the velocity of motion in the complex plane, is introduced to identify insignificant modes. Subsequently, admittance circle fitting theory is used to calculate the frequency, damping ratio, and gain of each mode. The accuracy of the parameter estimation is comprehensively improved through a segmented frequency band least-squares optimization method. Numerical simulations demonstrate that the proposed method can accurately extract modal parameters even in the presence of noise and disturbances, and the optimized frequency response curve shows a high degree of consistency with the theoretical model. The method's efficacy in a realistic noise environment is validated through a physical experiment, which successfully identifies the resonance peaks of insignificant modes. The resulting identified structural transfer function aligns well with the measured data, providing critical technical support for the high-performance autonomous control of ASP spacecraft.

Key words: autonomous parameter identification, ultra-high agility, stability, and precision spacecraft, modal parameter identification and optimization, admittance circle, Savitzky-Golay filter