六棱柱模块化可展开薄膜遮光罩设计与分析

doi:10.7527/S1000-6893.2025.31749

Abstract

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 conducted 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

CLC Number:

V476

Dake TIAN, Liyong ZHANG, Yongbin WANG, Jishou FANG, Lu JIN, Rongqiang LIU. Design and analysis of hexagonal prism modular deployable membrane sunshield[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(18): 431749.

Figures/Tables 20

Table 1

Fig.1

Fig.2

Fig.3

Fig.4

Fig.5

Fig.6

Fig.7

Fig.8

Fig.9

Fig.10

Fig.11

Fig.12

Fig.13

Fig.14

Table 2

Fig.15

Fig.16

Table 3

Storage rate of typical cylindrical sunshield

遮光罩	展开态高度/m	收纳率 $η$
MITAR遮光罩^［10-11］	0.56	4.0∶1
SEDOBA遮光罩^［12］	4.60	4.6∶1
CDST遮光罩^［13］	1.20	12.0∶1
充气遮光罩^［6］	1.10	5.5∶1
三级套筒遮光罩^［22］	0.60	2.3∶1
本研究遮光罩	3.51	11.7∶1

Table 3

Fig.17

References 36

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遮光罩名称	研究机构	遮光罩构型	驱动方式	展开态参数/m
IXO遮光罩^［8-9］	美国诺思罗普·格鲁曼公司	一维完整柱面	电机驱动	直径4 高度12
MITAR遮光罩^［10-11］	意大利航天局	一维完整柱面	弹性驱动	直径0.4 高度0.56
SEDOBA遮光罩^［12］	英国奎奈蒂克公司	一维局部柱面	电机+弹性驱动	直径3.9 高度4.6
CDST遮光罩^［13］	美国国家航空航天局	一维完整柱面	弹性驱动	直径0.2 高度1.2
充气遮光罩^［6］	浙江大学	一维完整柱面	充气驱动	直径0.3 高度1.1
套筒式遮光罩^［22］	中国科学院光电技术研究所	一维完整柱面	弹性驱动	直径0.28 高度0.6
二次展开遮光罩^［23］	中国科学院长春光学精密机械与物理研究所	一维局部柱面	电机驱动
高分7号遮光罩^［21］	北京空间机电研究所	一维局部柱面	弹性驱动	高度1.05
Gaia遮光罩^［14］	欧洲航天局	二维平面	弹性驱动	直径10.2
Starshade遮光罩^［15-16］	美国科罗拉多大学	二维平面	电机+弹性驱动	直径40
JPL遮光罩^［17］	美国喷气推进实验室	二维平面	电机驱动	直径5.5
JWST遮光罩^［18］	美国国家航空航天局联合欧洲航天局	二维平面	电机驱动	长×宽：14.6×21.2
燃料遮光罩^［19］	美国肯尼迪航天中心	三维锥面	充气驱动
ST-9遮光罩^［20］	美国国家航空航天局	三维锥面	电机+弹性驱动	宽度4

阶数	固有频率/Hz	振型描述
1	4.57	绕x₂轴弯曲
2	8.07	绕z₂轴扭转
3	14.86	绕y₂轴弯曲
4	19.50	绕z₂轴扭转
5	20.54	绕z₂轴扭转
6	23.40	绕z₂轴扭转
7	25.61	绕z₂轴扭转
8	26.10	绕y₂轴弯曲

Design and analysis of hexagonal prism modular deployable membrane sunshield

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