大型复杂航天器刚-液-柔耦合动力学研究

闫森; 岳宝增; 马伯乐

doi:10.21656/1000-0887.460040

大型复杂航天器刚-液-柔耦合动力学研究

doi: 10.21656/1000-0887.460040

北京理工大学宇航学院，北京 100081

基金项目:

国家自然科学基金（重点项目）（12132002）

详细信息

作者简介:
闫森（1997—），男，硕士(E-mail: 919786111@qq.com); 岳宝增(1962—)，男，教授，博士(通信作者. E-mail: bzyue@bit.edu.cn).

通讯作者:
岳宝增(1962—)，男，教授，博士(通信作者. E-mail: bzyue@bit.edu.cn).

中图分类号: O31
计量
- 文章访问数: 24
- HTML全文浏览量: 6
- PDF下载量: 6
- 被引次数: 0
出版历程
- 收稿日期: 2025-03-03
- 修回日期: 2025-12-16
- 网络出版日期: 2026-04-01
- 刊出日期: 2026-03-01

Coupling Dynamics Research of Large Complex Rigid-Liquid-Flexible Spacecrafts

School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, P.R.China

Funds:

The National Science Foundation of China(12132002)

摘要

摘要: 新一代航天器通常需要携带复杂的大尺寸柔性太阳帆板和大容量的液体燃料贮箱，以完成长时间及复杂的在轨飞行任务.航天器在机动和控制过程中会产生刚体运动、液体晃动及柔性附件振动之间的非线性耦合问题.该文基于Kirchhoff-Love板理论和有限元分析方法计算了柔性帆板振动，采用势函数理论计算了液体燃料晃动，借助Lagrange方法推导出刚-液-柔耦合系统的动力学模型，揭示了主刚体运动、液体晃动和柔性附件振动之间的耦合动力学特性.通过与已发表的实验和分析结果的比较，验证了所提出的刚-液-柔耦合航天器建模方法的有效性.考虑含有复杂大尺寸柔性太阳帆板的充液航天器耦合分析结果表明，有限元方法能够准确描述柔性附件高频模态的动态响应.同时，由于该类大型复杂空间结构部件的低频特性，与液体燃料晃动的耦合问题也更加突出.
- 液体晃动 /
- 复杂柔性附件 /
- 有限元方法 /
- 刚-液-柔耦合
Abstract: To accomplish long-duration and complex orbit flight missions, next-generation spacecrafts need to carry large flexible structures and high-capacity liquid fuel tanks. The nonlinear coupling problems between rigid body motion, liquid sloshing, and flexible structure vibrations become particularly significant during spacecraft maneuvering and control processes. A dynamic model for rigid-liquid-flexible coupling systems was presented, to first calculate the vibration of the flexible structure with the Kirchhoff-Love plate theory and the finite element methods. Then the flow theory was employed to model liquid fuel sloshing, and finally the overall dynamic model for the coupling system was derived with the Lagrange method. The study reveals the coupling dynamic interactions between rigid body motion, liquid sloshing, and flexible structure vibrations. The proposed modeling approach for rigid-liquid-flexible coupling spacecrafts was validated by comparison with published experimental and analytical results. The coupling analysis of complex, liquid-filled spacecrafts with large, flexible structures shows that, the finite element method can accurately capture the dynamic responses of high-frequency modes of the flexible structures. Additionally, due to the low-frequency characteristics of these large and complex space structures, the coupling effects with liquid fuel sloshing become even more pronounced.
- liquid sloshing /
- complex flexible structure /
- finite element method /
- rigid-liquid-flexible coupling

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