• CN:11-2187/TH
  • ISSN:0577-6686

机械工程学报 ›› 2023, Vol. 59 ›› Issue (13): 36-48.doi: 10.3901/JME.2023.13.036

• 机器人及机构学 • 上一篇    下一篇

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多构型组合式模块化可展开天线机构设计与分析

田大可1, 高海明1, 金路2, 范小东3, 刘荣强3, 郭振伟1, 赵丙峰4   

  1. 1. 沈阳建筑大学机械工程学院 沈阳 110168;
    2. 沈阳建筑大学土木工程学院 沈阳 110168;
    3. 哈尔滨工业大学机器人技术与系统国家重点实验室 哈尔滨 150001;
    4. 东北大学航空动力装备振动及控制教育部重点实验室 沈阳 110819
  • 收稿日期:2022-08-22 修回日期:2022-12-08 出版日期:2023-07-05 发布日期:2023-08-15
  • 通讯作者: 金路(通信作者),女,1982年出生,博士,教授,硕士研究生导师。主要研究方向为空间可展开天线结构动力学、高等钢结构可靠性。E-mail:jinlu@sjzu.edu.cn
  • 作者简介:田大可,男,1981年出生,博士,副教授,硕士研究生导师。主要研究方向为宇航空间折展机构、空天变体飞行器、航空发动机总体结构、装配式结构。E-mail:tiandake@sjzu.edu.cn;高海明,男,1998年出生,硕士研究生。主要研究方向为机器人与机构学、空间可展开天线机构。E-mail:gaohaiming@stu.sjzu.edu.cn
  • 基金资助:
    国家自然科学基金重点(51835002)、东北大学航空动力装备振动及控制教育部重点实验室研究基金(VCAME202207)、中国博士后科学基金(2019M661126)、辽宁省自然科学基金(2022-MS-278)和辽宁省教育厅基金(LJKZ0563)资助项目。

Design and Analysis of Multi-configuration Combined Modular Deployable Antenna Mechanism

TIAN Dake1, GAO Haiming1, JIN Lu2, FAN Xiaodong3, LIU Rongqiang3, GUO Zhenwei1, ZHAO Bingfeng4   

  1. 1. School of Mechanical Engineering, Shenyang Jianzhu University, Shenyang 110168;
    2. School of Civil Engineering, Shenyang Jianzhu University, Shenyang 110168;
    3. State Key Laboratory of Robotics and System, Harbin Institute of Technology, Harbin 150001;
    4. Key Laboratory of Vibration and Control of Aero-Propulsion System Ministry of Education, Northeastern University, Shenyang 110819
  • Received:2022-08-22 Revised:2022-12-08 Online:2023-07-05 Published:2023-08-15

摘要: 针对空间可展开天线大口径、高收纳率、高结构利用率等迫切发展需求,提出一种多构型组合式模块化可展开天线机构。首先,阐述了机构的总体方案,分别从模块组合规则、肋单元展收原理等对结构进行了详细分析,并基于机构学基本理论对机构的自由度进行了计算;其次,根据机器人学理论分别建立了单模块与多模块的运动学模型,利用空间等包络圆法求解出各肋单元夹角间的关系;同时采用数值仿真软件对多模块联动过程中肋单元夹角的变化规律进行了研究,对建立的多构型组合式模块化机构运动学模型进行了验证及分析;最后对比了单构型与多构型组合式两类天线的结构利用率、收纳率等关键参数,并研制了一台六棱柱单模块原理样机,开展了展开功能试验与验证。仿真及试验结果表明:所提出的机构能够实现由收拢至展开态的运动变化,展开过程中机构无干涉、卡滞等问题;同时,提出的新构型方案不仅保留了模块化结构通用性好、易拓展等特点,还具有较高的收纳率和结构利用率,研究成果对于丰富和发展宇航空间机构基础理论,推动该型天线的工程应用等具有较高的参考价值和借鉴意义。

关键词: 空间可展开天线, 组合式结构, 模块化设计, 运动学分析, 结构利用率

Abstract: A multi-configuration combined modular deployable antenna mechanism is proposed for the urgent development needs of space deployable antenna with large aperture, high stowage rate and high structural utilization. Firstly, the overall scheme of the mechanism is described, and the structure is analyzed in detail from the rules of module combination and the principle of rib unit deploying and stowing, and the degrees of freedom of the mechanism are calculated based on the basic theory of mechanism; secondly, the kinematic models of single module and multi-module are established respectively according to the theory of robotics, and the relationship between the angle of each rib unit is solved by the spatial equal envelope circle method; meanwhile, the numerical simulation software is used to study the change law of the rib unit angle during the linkage of multi-module. The kinematic model of the multi-configuration modular mechanism is verified and analysed. Finally, the key parameters such as structural utilization rate and stowage rate of the single configuration and multi-configuration antennas are compared, and a hexagonal single-module prototype is developed and the unfolding function is tested and verified. The simulation and test results show that the proposed mechanism can realize the change of motion from stowed to unfolded state, and there is no interference and jamming in the unfolding process. At the same time, the proposed new configuration not only retains the characteristics of good versatility and easy expansion of the modular structure, but also has high storage rate and structural utilization rate, and the research results have high reference value and significance for enriching and developing the basic theory of space mechanism and promoting the engineering application of this type of antenna.

Key words: space deployable antenna, combined structure, modular design, kinematic analysis, structural utilization rate

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