中国空间科学技术

中国空间科学技术 ›› 2025, Vol. 45 ›› Issue (6): 84-98.doi: 10.16708/j.cnki.1000-758X.2025.0091

• 论文 • 上一篇    下一篇

串链式太阳帆航天器进出地影刚-柔-热耦合动力学分析

彭奕翔1，刘铸永1，袁婷婷2，刘锦阳1,*，武云丽3   

  1. 1.上海交通大学 船舶海洋与建筑工程学院，上海200240
    2.广西大学 土木建筑工程学院，南宁530004
    3.北京控制工程研究所，北京100190
  • 收稿日期:2025-01-06 修回日期:2025-03-10 录用日期:2025-03-13 发布日期:2025-11-17 出版日期:2025-12-01

Rigid-flexible-thermal coupling dynamic analysis for solar sail in tandem during entering and exiting Earth’s shadow

PENG Yixiang1，LIU Zhuyong1，YUAN Tingting2，LIU Jinyang1,*，WU Yunli3   

  1. 1.School of Ocean and Civil Engineering, Shanghai Jiao Tong University, Shanghai 200240, China
    2.School of Civil Engineering and Architectural, Guangxi University, Nanning 530004, China
    3.Beijing Institute of Control Engineering & Key Laboratory of Space Intelligent Control Technology, Beijing 100190, China
  • Received:2025-01-06 Revision received:2025-03-10 Accepted:2025-03-13 Online:2025-11-17 Published:2025-12-01

PDF (PC)

2

摘要： 针对串链式太阳帆航天器在轨进出地影期间冷热交变引起的航天器热致振动问题，提出一种刚柔热耦合的动力学建模方法。首先推导了柔性板的动力学变分方程和热传导方程，然后同时考虑中心刚体姿态角、帆板转角、帆板弹性变形以及进出地影对太阳辐射热流密度的影响,基于单向递推组集的方法建立了串链式太阳帆航天器的多物理场耦合动力学模型。采用铰相对坐标和模态坐标缩减自由度，有效提升了计算效率。仿真结果表明，在航天器进入阴影区和重新进入阳照区时，中心刚体的角速度和太阳帆板的挠度均会产生明显的振动，振幅随着换热系数增大而减小，振动衰减后帆板温度接近于环境温度。揭示了多源耦合振动对系统运动稳定性的影响规律，为变温度场下串链式太阳帆航天器的姿态控制建立基础。

关键词: 串链式太阳帆航天器, 进出地影, 刚-柔-热耦合, 动力学, 单向递推组集方法

Abstract: To investigate the thermally induced vibration problem of solar sail in tandem caused by the alternating thermal environments during the period of entering and exiting the Earth’s shadow, a rigid-flexible-thermal coupling dynamic modeling method is proposed. Firstly, the dynamic variational equations and heat conduction equations of the flexible solar plate are derived, and then the multi-physics coupling dynamic model of solar sail in tandem is established based on forward recursive formulation, considering the influences of the attitude angles of central rigid-body and solar plates, elastic deformations, and the Earth’s shadow on the solar radiation heat flux. The use of the joint relative coordinates and the modal coordinates can reduce the system degrees of freedom, such that the computational efficiency is improved a lot. Simulation results indicate that when the spacecraft enters and leaves the Earth’s shadow, significant vibrations of the central rigid-body angular velocity and the solar plate deflection are induced, and that the vibration amplitude decreases with the increase of the convective heat transfer coefficient. The stable temperature after the attenuation of the vibration approaches the environment temperature. The proposed method reveals the influence of multi-source coupled vibration on the stability of system motion, which lays a foundation for the attitude control of solar sail in tandem in variable temperature environment.

Key words: solar sail in tandem, entering and exiting the Earth's shadow, rigid-flexible-thermal coupling, dynamics, forward recursive formulation