复合材料卫星承力筒连接结构分析

于成月; 刘波; 李传政; 薛闯

doi:10.7527/S1000-6893.2021.25161

航空学报 >

2022 , Vol. 43 >Issue 3: 225161 - 225161

DOI: https://doi.org/10.7527/S1000-6893.2021.25161

固体力学与飞行器总体设计

复合材料卫星承力筒连接结构分析

于成月 ,
刘波 ,
李传政 ,
薛闯

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1. 中国科学院长春光学精密机械与物理研究所, 长春 130033;
2. 中国科学院大学, 北京 100049

收稿日期: 2020-12-25

修回日期: 2021-01-11

网络出版日期: 2021-01-26

基金资助

国家自然科学基金（11903034）

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Analytical research on connecting structure of composite material satellite bearing cylinder

YU Chengyue ,
LIU Bo ,
LI Chuanzheng ,
XUE Chuang

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1. Changchun Institute of Optics, Fine Mechanics and Physics, Chinese Academy of Sciences, Changchun 130033, China;
2. University of Chinese Academy of Sciences, Beijing 100049, China

Received date: 2020-12-25

Revised date: 2021-01-11

Online published: 2021-01-26

Supported by

National Natural Science Foundation of China (11903034)

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摘要

大型卫星承力筒的连接结构损伤是设计时必须要考虑的关键问题，以某碳纤维复合材料卫星承力筒的连接结构为研究对象，应用ABAQUS有限元软件建立复合材料层合板连接结构渐进损伤模型，并且根据Hashin失效准则及Tserpes材料性能退化准则，应用Fortran语言二次开发了UMAT子程序，研究承力筒层合板螺栓连接及胶螺混合连接的失效机制；在此基础上，利用仿真分析螺栓连接结构的刚度探究对卫星承力筒试验件力学性能的影响。结果表明:利用螺栓连接结构刚度进行仿真建模的卫星承力筒试验件结果更接近试验值，其误差相比于多点约束—MPC单元减小了4%~9%，说明此方法能更好地满足仿真分析要求。该分析方法为复合材料卫星承力筒连接结构的力学性能及多螺栓连接结构的有限元仿真分析提供一定参考，适用于具有连接结构的卫星力学分析。

关键词： 卫星承力筒; 复合材料; 渐进损伤模型; 连接结构; 胶层; 有限元分析

本文引用格式

于成月 , 刘波 , 李传政 , 薛闯 . 复合材料卫星承力筒连接结构分析[J]. 航空学报, 2022 , 43(3) : 225161 -225161 . DOI: 10.7527/S1000-6893.2021.25161

Abstract

The connection structure damage of large satellite bearing cylinders is a key issue requiring consideration in the design.Taking the connection structure of a carbon fiber composite satellite bearing cylinder as the research object, we use the ABAQUS finite element software to establish the progressive damage model of the composite material laminate bolt connection.Based on the Hashin failure criterion and the Tserpes material performance degradation criterion, the Fortran language is adopted to develop the UMAT subroutine for the second time to study the failure mechanism of the bearing cylinder laminate bolt connection and the rubber-screw hybrid connection.In addition, the simulation analysis of the stiffness of the bolted connection structure is used to explore the impact on the mechanical properties of the satellite bearing cylinder test piece.The results show that the simulation of the satellite bearing cylinder test piece using the bolt connection structure stiffness for simulation modeling is closer to the experimental value, and compared with the MPC connection, the error is reduced by 4%-9%, indicating that this method better meets the requirements of simulation analysis.This analysis method provides reference for the mechanical property analysis of the composite satellite bearing cylinder connection structure and finite element simulation analysis of the multi-bolt connection structure, and is applicable for mechanical analysis of satellites with connected structures.

Key words： satellite bearing cylinders; composite; progressive damage model; connection structure; adhesive layer; finite element analysis

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