Modeling of Biaxial Compression Behavior of Carbon Fiber-Reinforced Composite after Low-Velocity Impact

被引：5

作者：

Yang, Bin ^{[1
]}

Fu, Kunkun ^{[1
]}

Li, Yan ^{[1
]}

机构：

[1] Tongji Univ, Sch Aerosp Engn & Appl Mech, Shanghai 200092, Peoples R China

来源：

JOURNAL OF AEROSPACE ENGINEERING | 2022年 / 35卷 / 03期

基金：

中国博士后科学基金;

关键词：

Carbon fiber-reinforced composite (CFRC); Biaxial compression; Compression after impact (CAI) strength; Finite element (FE); GROWTH PHENOMENA; DAMAGE; FAILURE; PANELS; DELAMINATION; SIMULATION; CRITERION; EVOLUTION; LAMINATE; TENSILE;

D O I：

10.1061/(ASCE)AS.1943-5525.0001417

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

This study presents a finite-element (FE) model considering intralaminar damage and interlaminar delamination to predict the biaxial compression behavior of carbon fiber-reinforced composites (CFRCs) with low-velocity impact damage. First, the FE model was validated by a uniaxial compression experiment. The FE predictions in terms of compression after impact (CAI) strength and failure patterns were consistent with the experimental results. Then the validated FE model was used to predict the biaxial compression behavior of the CFRCs. It was found that the residual strength of the CFRCs was dependent on the buckling mode of the laminate due to the coupling effect of the longitudinal and transverse compressive loadings. Correspondingly, the CAI strength under biaxial compression was lower than that under longitudinal or transverse compressive loading.

引用

页数：12

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