A novel creep-fatigue stiffness degradation model for composite materials

2020 ◽  
Vol 237 ◽  
pp. 111955 ◽  
Author(s):  
Seyed Sina Samareh-Mousavi ◽  
Fathollah Taheri-Behrooz
Keyword(s):  
Composite Materials ◽  
Stiffness Degradation ◽  
Degradation Model ◽  
Creep Fatigue

Numerical Simulation of Unidirectional Hoop Composite Laminates under Flexural Loads

2007 ◽  
Vol 334-335 ◽  
pp. 217-220
Author(s):  
Li Li Tong ◽  
Zhen Qing Wang ◽  
Bao Hua Sun
Keyword(s):  
Numerical Simulation ◽  
Composite Laminates ◽  
Calculated Result ◽  
Composite Laminate ◽  
Stiffness Degradation ◽  
Test Results ◽  
Degradation Model ◽  
Compressive Stresses

Numerical simulation for unidirectional hoop composite laminates under flexural loads was finished. The change of tensile and compressive stresses, the position of local crush and delamination and stiffness degradation were analyzed with parametric program compiled by APDL language in ANSYS. The results showed that composite laminate could bear the load continually after local crush and delamination. Displacements of calculated result with stiffness degradation model matched test results well.

Progressive failure analysis of marine sandwich joints with a modified material degradation model

2018 ◽  
Vol 38 (9) ◽  
pp. 426-438
Author(s):  
Mengzhen Li ◽  
Renjun Yan ◽  
Wei Shen ◽  
Kang Liu
Keyword(s):  
Failure Analysis ◽  
Progressive Failure ◽  
Woven Fabric ◽  
Stiffness Degradation ◽  
Displacement Curve ◽  
Material Degradation ◽  
Degradation Model ◽  
Failure Patterns ◽  
Progressive Failure Analysis ◽  
Load Displacement

The progressive failure analysis based on a modified stiffness degradation model was proposed to predict mechanical response of sandwich L-joints for ships. A representative volume element was established for the derivation of the modified material degradation model for two-dimensional orthogonal woven fabric structures based on micromechanical theory. The modified Shokrieh failure criterion and six field variables were applied in ABAQUS user subroutines. Three different coordinate systems were used to assign reasonable material orientation. The predictions of ultimate load, stress distribution, load-displacement curve and failure patterns were compared with experimental results. The good consistence indicates the effectiveness of the proposed stiffness degradation model. The FE results show the edge of the arc bracket is the stress concentration area due to the shear lag effect, and the declined slope of load–displacement curve is caused by delamination failure due to the stiffness difference of laminates and foam core.

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