大型空间薄膜遮阳罩折展构型设计与分析

doi:10.3901/JME.2020.05.013

机械工程学报 ›› 2020, Vol. 56 ›› Issue (5): 13-20.doi: 10.3901/JME.2020.05.013

• 航天重器——空间大型可展机构与装备专刊 • 上一篇下一篇

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大型空间薄膜遮阳罩折展构型设计与分析

林秋红¹, 张骞², 贾文文¹, 邱慧¹, 王馨玉², 蔡建国²

1. 北京空间飞行器总体设计部北京 100094;
2. 东南大学国家预应力工程技术中心南京 211100

收稿日期:2019-01-03 修回日期:2019-10-09 出版日期:2020-03-05 发布日期:2020-04-23
通讯作者: 蔡建国(通信作者),男,1984年出生,博士,教授,博士研究生导师。主要研究方向为新型折叠与展开结构、折纸结构。E-mail:j.cai@seu.edu.cn
作者简介:林秋红,女,1985年出生,高级工程师。主要研究方向为空间大型桁架结构和柔性可展开结构技术。E-mail:15010362810@163.com
基金资助:
国家自然科学基金优秀青年基金（51822805）、江苏省自然科学基金优秀青年基金（BK20170083）和“十三五”民用航天预研项目（D020205）资助项目。

Deployable Configuration Design and Analysis of Large Space Membrane Sunshield Structures

LIN Qiuhong¹, ZHANG Qian², JIA Wenwen¹, QIU Hui¹, WANG Xinyu², CAI Jianguo²

1. Beijing Institute of Spacecraft System Engineering, Beijing 100094;
2. National Prestress Engineering Research Center, Southeast University, Nanjing 211100

Received:2019-01-03 Revised:2019-10-09 Online:2020-03-05 Published:2020-04-23

摘要/Abstract

摘要： 将折纸技术应用于空间薄膜结构构型设计并在展开全过程进行应力优化，设计折纸型充气管结构组合使用，完成大型空间薄膜遮阳罩折展构型设计。基于光学系统遮阳需求，采用杆系等效方法分析了两种薄膜折痕方案折展过程中的应力改变水平，并进行了遮阳罩薄膜结构的参数设计。考虑到充气管与薄膜结构的点连接和同步折展问题，采用单顶点六折痕模式改进了传统的Z字型充气管设计方案并进行了通气性能分析。采用ANSYS/LS-DYNA仿真计算了薄膜结构和充气管结构的展开全过程，并进行了应力水平和气压分析，最终通过样机模型进行了展开试验验证。结果表明，组合采用改进薄膜折痕方案和改进Z字型充气管方案，大型空间薄膜遮阳罩的展开路径明确，收纳比高且不会造成遮阳薄膜损伤。

关键词: 薄膜遮阳罩, 折纸, 杆系等效方法, 展开过程, 样机

Abstract: Origami technology is applied to the configuration design of space membrane structures and the stress optimization is conducted in the whole deployment process. Combined with origami-type inflatable tube, configuration of large space deployable membrane sunshield structure is designed. The stress level in whole deployment process of two kinds of configuration design scheme is analyzed by using truss equivalent method. The parameters of membrane sunshield structures are identified based on the sunshade demand of optical systems. Considering the point junction and synchronous deployment between inflatable tube and membrane, a novel design scheme of inflatable tube is proposed inspired by single-vertex six-creases origami pattern and the ventilation characteristic of which is analyzed. ANSYS/LS-DYNA is used to simulate the whole deployment process of the membrane structure and the inflatable tube, and the configuration, the stress level and pressure are monitored and analyzed. Finally, the prototype is made to conduct the deployment experiment verification. The results show the large space membrane sunshield structure composed of the improved crease design scheme of membrane structures and inflatable tubes has clear deployment path and high storage ratio and there is no damage in the membrane structure.

Key words: membrane sunshield structures, origami, truss equivalent method, deployable process, prototype

中图分类号:

V445

林秋红, 张骞, 贾文文, 邱慧, 王馨玉, 蔡建国. 大型空间薄膜遮阳罩折展构型设计与分析[J]. 机械工程学报, 2020, 56(5): 13-20.

LIN Qiuhong, ZHANG Qian, JIA Wenwen, QIU Hui, WANG Xinyu, CAI Jianguo. Deployable Configuration Design and Analysis of Large Space Membrane Sunshield Structures[J]. Journal of Mechanical Engineering, 2020, 56(5): 13-20.

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大型空间薄膜遮阳罩折展构型设计与分析

Deployable Configuration Design and Analysis of Large Space Membrane Sunshield Structures

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