Deployment analysis of composite thin-walled lenticular tubes with effect of storage time and temperature  

作　　者：Jinfeng DENG Ning AN Qilong JIA Xiaofei MA 

机构地区：[1]School of Aeronautics and Astronautics,Sichuan University,Chengdu 610065,China [2]State Key Laboratory for Strength and Vibration of Mechanical Structures,School of Aerospace,Xi’an Jiaotong University,Xi’an 710049,China [3]State Key Laboratory of Structural Analysis for Industrial Equipment,Dalian University of Technology,Dalian 116024,China [4]Xi’an Institute of Space Radio Technology,Xi’an 710100,China

出　　处：《Chinese Journal of Aeronautics》2024年第1期162-172,共11页中国航空学报（英文版）

基　　金：co-supported by the National Natural Science Foundation of China(No.12202295);the Fundamental Research Funds for the Central Universities,China(No.YJ2021137);the Open Project of State Key Laboratory for Strength and Vibration of Mechanical Structures,Xi’an Jiaotong University,China(No.SV2021-KF-04);the Open Project of State Key Laboratory of Structural Analysis for Industrial Equipment,Dalian University of Technology,China(No.GZ22120)。

摘　　要：Composite Thin-walled Lenticular Tube(CTLT)is increasingly utilized in small satellites missions as a lightweight,foldable,and rollable structural material that facilitates the construction of large deployable systems.The CTLT is initially flattened and coiled around a central hub for storage before launch,during which elastic energy is stored as deformation energy,allowing it to be self-deployed on demand for use in orbit.This work presents a comprehensive investigation into the coiling,storage and deployment behaviors of CTLT that wraps around a central hub.A nonlinear explicit dynamic finite element model was developed with both deformable CTLT and rigidbodies mechanisms including the central hub and guide rollers,as well as the complex interactions among them.The coiling mechanics characteristics such as stored strain energy and rotational moment were presented and validated against experimental data in the literature.Then,the dynamic deployment behaviors were analyzed in terms of two different deployment methods,namely,controlled deployment and free deployment.The effect of material property change during storage was also discussed through numerical experiments.

关 键 词：Composite deployable structures Deployment dynamics Finite element method Stress relaxation Thin-walled booms 

分 类 号：V414.8[航空宇航科学与技术—航空宇航推进理论与工程]