六棱柱模块化可展开薄膜遮光罩设计与分析

田大可; 张立永; 王永滨; 方纪收; 金路; 刘荣强

doi:10.7527/S1000-6893.2025.31749

航空学报 >

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DOI: https://doi.org/10.7527/S1000-6893.2025.31749

六棱柱模块化可展开薄膜遮光罩设计与分析

田大可 ,
张立永 ,
王永滨 ,
方纪收 ,
金路 ,
刘荣强

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1. 沈阳建筑大学
2. 北京空间机电研究所
3. 沈阳建筑大学土木工程学院
4. 哈尔滨工业大学机电学院

收稿日期: 2025-01-02

修回日期: 2025-06-07

网络出版日期: 2025-06-27

基金资助

辽宁省自然科学基金面上项目;辽宁省教育厅基本科研项目;中国航天科技集团有限公司航天进入减速与着陆技术实验室开放课题;国家自然科学基金联合基金项目

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Design and Analysis of Hexagonal Prism Modular Deployable Membrane Sunshield

TIAN Da-Ke ,
ZHANG Li-Yong ,
WANG Yong-Bin ,
FANG Ji-Shou ,
JIN Lu ,
LIU Rong-Qiang

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Received date: 2025-01-02

Revised date: 2025-06-07

Online published: 2025-06-27

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摘要

空间可展开遮光罩是抑制消除杂散光、防止外热流进入、提高光学系统成像质量的关键航天装备，是空间科学、深空探测等学术研究和实际应用的前沿与热点。针对探月、探火、星际探测等对大尺度、高收纳率遮光罩的迫切需求，提出一种可实现尺度灵活拓展的模块化可展开柱状遮光罩构型方案。首先，基于模块化思想，以Sarrus机构为基本构型开展了冗余驱动可展开支撑机构刚柔耦合多体系统设计，阐述了机构展收及锁定刚化机理，并采用空间几何坐标法分析了机构展开过程中关键节点的运动规律；其次，采用ABAQUS仿真软件建立了不同参数下单层可展开薄膜收拢态有限元模型，探究了不同参数对薄膜结构展开过程力学特性的影响规律，优选确定出最终设计参数，并开展了多层薄膜展开过程动力学仿真，分析了展开过程薄膜应力变化规律；再次，建立了遮光罩整体完全展开态有限元模型，开展了结构模态分析，研究了固有频率及振型变化规律；最后，研制了多模块遮光罩原理样机，并在微重力试验装置上对遮光罩进行了展开功能试验。研究结果表明：所设计的遮光罩能够有效实现展开与锁定功能，机构与薄膜展开过程协调、无干涉，验证了所提原理及方案的正确性。该研究可为同类航天器遮光罩的研究提供理论基础和技术参考。

关键词： 模块化结构; 薄膜遮光罩; 运动学分析; Kresling折纸; 结构设计

本文引用格式

田大可 , 张立永 , 王永滨 , 方纪收 , 金路 , 刘荣强 . 六棱柱模块化可展开薄膜遮光罩设计与分析[J]. 航空学报, 0 : 1 -0 . DOI: 10.7527/S1000-6893.2025.31749

Abstract

The deployable sunshield is a critical aerospace device for suppressing and eliminating stray light, preventing external heat flux intrusion, and improving the imaging quality of optical systems. It is a forefront and hotspot in academic research and practical applications in space science and deep space exploration. To address the urgent demands for large-scale, high-storage-ratio sunshields in lunar exploration, Mars exploration, and interstellar missions, a modular scalable cylindrical sunshield configuration is proposed. Firstly, based on the modular concept, a redundantly driven deployable support mechanism with a rigid-flexible coupled multibody system is developed using the Sarrus mechanism as the fundamental configuration. The deployment, retraction, locking, and stiffening mechanisms of the structure are explained, and the spatial geometric coordinate method is employed to analyze the motion patterns of key nodes during the deployment process. Secondly, finite element models of single-layer folded membranes under various parameters are established using ABAQUS to investigate parameter effects on mechanical behavior during deployment. Optimal design parameters are determined through comparative analysis, followed by dynamic simulations of multilayer membrane deployment processes to characterize stress evolution patterns. Thirdly, a finite-element model of the fully deployed state of the entire sunshield is established, and a structural modal analysis is carried out to analyze the variation laws of the natural frequency and vibration mode. Finally, a multi-module sunshield prototype is developed, and deployment functionality tests are conducted on a microgravity test platform. The results show that the designed sunshield effectively achieves deployment and locking functions, with coordinated and interference-free deployment of the mechanism and membrane, thereby verifying the correctness of the proposed principle and design. This study provides a theoretical foundation and technical reference for research on similar spacecraft sunshields.

Key words： modular structure; membrane sunshield; kinematics analysis; Kresling origami; structural design

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