中国空间科学技术

中国空间科学技术 ›› 2025, Vol. 45 ›› Issue (3): 120-130.doi: 10.16708/j.cnki.1000.758X.2025.0044

• 论文 • 上一篇    下一篇

基于周期微小激励的引力波探测航天器质心辨识#br#

王子鸣1，黎明2，姚金铭3，齐超群1，张慧博4,*，张浩1   

  1. 1.河北工业大学 机械工程学院，天津300401
    2.航天东方红卫星有限公司，北京100094
    3.哈尔滨工业大学 航天学院，哈尔滨150001
    4.哈尔滨工程大学 机电工程学院，哈尔滨150001
  • 收稿日期:2024-02-25 修回日期:2024-05-10 录用日期:2024-05-13 发布日期:2025-05-15 出版日期:2025-06-01

Identification of center of mass for gravitational wave detection spacecraft based on periodical micro incentives

WANG Ziming1， LI Ming2， YAO Jinming3， QI Chaoqun1， ZHANG Huibo4,*， ZHANG Hao1   

  1. 1.School of Mechanical and Engineering, Hebei University of Technology， Tianjin 300401， China
    2.DFH Satellite Co.,  Ltd.， Beijing 100094， China
    3.School of Astronautics, Harbin Institute of Technology， Harbin 150001， China
    4.College of Mechanical and Electrical Engineering, Harbin Engineering University， Harbin 150001， China
  • Received:2024-02-25 Revision received:2024-05-10 Accepted:2024-05-13 Online:2025-05-15 Published:2025-06-01

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摘要： 受燃料消耗与结构热变形等因素的影响，空间引力波探测航天器的质量分布会发生变化，质心位置也会发生偏移，严重影响引力波探测精度。面向空间引力波探测航天器高精度质心测量的需求，提出一种基于周期性微小激励的航天器质心辨识方法。首先，构建了考虑空间非保守力、重力梯度力及推力器噪声影响的航天器动力学模型。然后，开展了基于空间惯性传感器与星敏感器测量数据的惯性张量辨识及基于推力器周期性微小激励输入方法研究，提出了基于周期微小激励与卡尔曼滤波理论的质心辨识方法。最后，进行了不同周期激励下的仿真模拟验证。仿真结果表明，在三角波形的力矩下，提出的方法能够在2.2×10-5 rad极小角度机动下实现2.14×10-6m的高精度质心辨识，从而降低星间链路重建成本，为维持空间引力波探测精度提供了技术途径。

关键词: 质心辨识, 引力波探测航天器, 周期微小激励, 空间非保守力, 卡尔曼滤波

Abstract:  Due to the influence of factors such as fuel consumption and structural thermal deformation, the mass distribution of the space-based gravitational wave detection spacecraft will change, and the position of the center of mass will be offset, which will seriously affect the accuracy of gravitational wave detection. Aiming at the demand of high-precision measurement of center of mass for the space-based gravitational wave detection spacecraft, a spacecraft center of mass identification method based on periodical micro incentives is proposed. First, a spacecraft dynamics model that takes into account the effects of nonconservative forces in space, gravity gradient forces and thruster noise is constructed. Then, the research on inertia tensor identification method based on space inertial sensor and star sensor measurement data, and the input method of periodic micro incentives based on thrusters are conducted. A center of mass identification method based on periodical micro incentives and Kalman filter theory is proposed. Finally, simulations under different waves of incentives are carried out. The results show that under the moment of the triangular waveform, the present method is able to achieve high-precision centroid identification with a resolution of 2.14×10-6m during an extremely small angular maneuver of 2.2×10-5rad. This research can reduce the cost of interplanetary link reconstruction and provide a technical approach to maintain the accuracy of spacecraft detection.

Key words: identification of center-of-mass, gravitational wave detection spacecraft, periodical micro incentives, non-conservative force, Kalman filter