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

被引:0
作者
Zhao, Guoyang [1 ]
Shi, Jian [2 ]
Xu, Wei [1 ]
Sun, Nan [3 ]
Zeng, Jianjiang [4 ]
Yang, Guang [5 ]
Song, Kun [6 ]
Zheng, Jie [7 ]
机构
[1] Chengdu Aeronaut Polytech, Sch Aviat Maintenance Engn, Chengdu 610100, Peoples R China
[2] Civil Aviat Flight Univ China, Coll Aviat Engn, Guanghan 618307, Peoples R China
[3] Univ Alberta, Dept Elect & Comp Engn, Edmonton, AB T6G 2V4, Canada
[4] Nanjing Univ Aeronaut & Astronaut, Coll Aerosp Engn, Nanjing 210016, Peoples R China
[5] Jiangnan Univ, Sch Fiber Engn & Equipment Technol, Wuxi 214000, Peoples R China
[6] Nanjing Tech Univ, Sch Mech & Power Engn, Nanjing 211816, Peoples R China
[7] Univ Alberta, Dept Mech Engn, Edmonton, AB T6G 2R3, Canada
关键词
failure analysis; composite skin-stringer structures; load transfer; Hashin initiation criteria; Tserpes degradation law; PANELS;
D O I
10.3390/ma18061380
中图分类号
O64 [物理化学(理论化学)、化学物理学];
学科分类号
070304 ; 081704 ;
摘要
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.
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页数:15
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