中国空间科学技术

中国空间科学技术 ›› 2025, Vol. 45 ›› Issue (4): 144-153.doi: 10.16708/j.cnki.1000-758X.2025.0066

• 论文 • 上一篇    下一篇

模块化可展开天线结构刚柔耦合设计与驱动力分析

田大可1，张昊1，王永滨2，方纪收2，金路3,*，石祖玮1，范小东4   

  1. 1.沈阳建筑大学 机械工程学院，沈阳110168
    2.北京空间机电研究所，北京100094
    3.沈阳建筑大学 土木工程学院，沈阳110168
    4.哈尔滨工业大学 机器人技术与系统全国重点实验室，哈尔滨150001
  • 收稿日期:2024-03-07 修回日期:2024-05-10 录用日期:2024-06-13 发布日期:2025-07-22 出版日期:2025-08-01

Rigid-flexible coupling design and driving force analysis of modular deployable antenna structure

TIAN Dake1, ZHANG Hao1, WANG Yongbin2, FANG Jishou2, JIN Lu3,*, SHI Zuwei1, FAN Xiaodong4   

  1. 1.School of Mechanical Engineering, Shenyang Jianzhu University, Shenyang 110168, China
    2.Beijing Institute of Space Mechanics＆Electricity, Beijing 100094, China
    3.School of Civil Engineering, Shenyang Jianzhu University, Shenyang 110168, China
    4.State Key Laboratory of Robotics and Systems, Harbin Institute of Technology, Harbin 150001, China
  • Received:2024-03-07 Revision received:2024-05-10 Accepted:2024-06-13 Online:2025-07-22 Published:2025-08-01

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摘要： 模块化可展开天线具有通用性好、适应性强、拓展灵活等特点，是满足未来大尺度天线在轨装配、在轨建造等需求的一种具有较大发展潜力的构型形式。为更好地掌握六棱柱模块化可展开天线在轨展开过程中结构的力学特性，开展了天线结构刚柔耦合设计及驱动力分析。首先，开展了模块化可展开天线结构方案设计，阐述了结构组成及展收原理。其次，基于解析几何方法，建立了等效包络圆数学模型，求得了肋单元夹角等关键参数，并建立了可展开天线结构三维模型。再次，对上弦杆、斜腹杆、下弦杆等径向长杆进行柔性化处理，采用多体动力学仿真软件建立了模块化可展开天线机构刚柔耦合多体动力学模型。最后，分别从有重力、无重力两个方面对单模块、多模块天线在不同约束位置下的展开驱动力的变化规律进行了分析。研究结果表明：展开过程若存在重力，则约束位置的选择对驱动力影响较大；若不存在重力，则天线约束位置对展开影响较小。所开展的结构设计及多方案驱动力分析可为该型天线的样机研制及工程化应用提供一定的借鉴和参考。

关键词: 可展开天线, 模块化结构, 刚柔耦合结构, 空间几何建模, 驱动力分析

Abstract: Modular deployable antenna has the characteristics of good versatility, strong adaptability and expansion flexibility, and is a configuration form with great development potential to meet the needs of in-orbit assembly and construction of large-scale antenna in the future. In order to better grasp the mechanical characteristics of the antenna structure, the rigid-flexible coupling design and driving force analysis of the antenna structure are developed. Firstly, a scheme design of modular deployable antenna structure is carried out, and the structure composition and deployment/stowed principles are described. Secondly, based on the analytical geometric method, a mathematical model of the equivalent envelope circles is developed, and key parameters such as the angle of the rib unit are obtained, then the three-dimensional model of deployable antenna structure is established. Thirdly, the flexible processing of radial long beams such as upper beam, diagonal beam and lower beam is carried out, and a multi-body dynamic model of rigid-flexible coupling of modular deployable antenna mechanism is established by multi-body dynamics simulation software. Finally, the change laws of the deployable driving force of single module and multi module antennas at different confinement positions are analyzed from the aspects of gravity and no gravity. The results show that if there is gravity in the deploying process, the choice of constraint position has a great influence on the driving force. In the absence of gravity, the antenna constraint position has little effect on deployment. The structural design and multi scheme driving force analysis can provide some reference for the prototype development and engineering application of this antenna.

Key words: deployable antenna, modular structure, rigid-flexible coupling structure, space geometry modeling, driving force analysis