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复合蒙皮-桁条结构在压缩载荷下的失效行为与力传递研究

A Study on the Failure Behavior and Force Transmission of Composite Skin-Stringer Structures Under a Compressive Load.

作者信息

Zhao Guoyang, Shi Jian, Xu Wei, Sun Nan, Zeng Jianjiang, Yang Guang, Song Kun, Zheng Jie

机构信息

School of Aviation Maintenance Engineering, Chengdu Aeronautic Polytechnic, Chengdu 610100, China.

College of Aviation Engineering, Civil Aviation Flight University of China, Guanghan 618307, China.

出版信息

Materials (Basel). 2025 Mar 20;18(6):1380. doi: 10.3390/ma18061380.

DOI:10.3390/ma18061380
PMID:40141663
原文链接:https://pmc.ncbi.nlm.nih.gov/articles/PMC11943467/
Abstract

Carbon fiber-reinforced composite stringers, which support aircraft skins in resisting tensile, compressive, and shear loads, are widely used in aircraft structures. These composite structures play a crucial role in enhancing the performance and safety of the structural integration of aircrafts. To better understand the load-bearing capacity of composite stringer structures, this study developed a novel model to study the complex failure and load transmission behavior of T800/3900S-2B fiber-reinforced composite skin-stringer structures under compressive loading. Compression strength tests were conducted on a composite stringer/skin structure, and a three-dimensional FEM was developed using Abaqus/Standard 2022. The model incorporated the modified 3D Hashin initiation criteria and Tserpes degradation law through a UMAT subroutine, which can effectively capture the in-plane ply failure and interlaminar damage. The results revealed a high degree of similarity between the load-displacement curves and failure modes (i.e., matrix compressive cracking, fiber compressive failure, and fiber-matrix shear-out failure) obtained from the simulations and those from the experiments. This study provides an efficient and accurate model to simulate the failure and load transfer of composite skin-stringer structures, offering significant advancements in understanding and predicting the behavior of these critical components.

摘要

碳纤维增强复合材料纵梁用于支撑飞机蒙皮以抵抗拉伸、压缩和剪切载荷，在飞机结构中广泛应用。这些复合材料结构在提高飞机结构集成的性能和安全性方面发挥着关键作用。为了更好地理解复合材料纵梁结构的承载能力，本研究开发了一种新型模型，以研究T800/3900S - 2B纤维增强复合材料蒙皮 - 纵梁结构在压缩载荷下的复杂失效和载荷传递行为。对一种复合材料纵梁/蒙皮结构进行了压缩强度试验，并使用Abaqus/Standard 2022开发了三维有限元模型。该模型通过一个用户材料子程序（UMAT）纳入了改进的三维Hashin起始准则和Tserpes退化定律，能够有效捕捉面内铺层失效和层间损伤。结果表明，模拟得到的载荷 - 位移曲线和失效模式（即基体压缩开裂、纤维压缩失效和纤维 - 基体剪切失效）与实验结果高度相似。本研究提供了一个高效且准确的模型来模拟复合材料蒙皮 - 纵梁结构的失效和载荷传递，在理解和预测这些关键部件的行为方面取得了重大进展。

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