TY - JOUR
T1 - Constitutive modelling of composite laminates under uniaxial compression
AU - HU, Hsuan Teh
AU - KE, Lung Shen
N1 - Publisher Copyright:
© 2019 Chinese Society of Aeronautics and Astronautics
PY - 2019/4
Y1 - 2019/4
N2 - A nonlinear constitutive model for a single lamina is proposed for the failure analysis of composite laminates. In the material model, both fiber and matrix are assumed to behave elastic-plastically and the in-plane shear is assumed to behave nonlinearly with a variable shear parameter. The damage onset for individual lamina is detected by a mixed failure criterion, composed of the Tsai-Wu criterion and the maximum stress criterion. After damage takes place within the lamina, the fiber and in-plane shear are assumed to exhibit brittle behavior, and the matrix is assumed to exhibit degrading behavior. The proposed nonlinear material model is tested against experimental data of composite laminates subjected to uniaxial compressive loads, and good agreement is obtained.
AB - A nonlinear constitutive model for a single lamina is proposed for the failure analysis of composite laminates. In the material model, both fiber and matrix are assumed to behave elastic-plastically and the in-plane shear is assumed to behave nonlinearly with a variable shear parameter. The damage onset for individual lamina is detected by a mixed failure criterion, composed of the Tsai-Wu criterion and the maximum stress criterion. After damage takes place within the lamina, the fiber and in-plane shear are assumed to exhibit brittle behavior, and the matrix is assumed to exhibit degrading behavior. The proposed nonlinear material model is tested against experimental data of composite laminates subjected to uniaxial compressive loads, and good agreement is obtained.
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U2 - 10.1016/j.cja.2019.02.003
DO - 10.1016/j.cja.2019.02.003
M3 - Article
AN - SCOPUS:85062287775
VL - 32
SP - 938
EP - 947
JO - Chinese Journal of Aeronautics
JF - Chinese Journal of Aeronautics
SN - 1000-9361
IS - 4
ER -