Exploiting the structural reserve of textile composite structures by progressive failure analysis using a new orthotropic failure criterion

2011 ◽  
Vol 89 (11-12) ◽  
pp. 1214-1223 ◽  
Author(s):  
Raimund Rolfes ◽  
Matthias Vogler ◽  
Steffen Czichon ◽  
Gerald Ernst
Keyword(s):  
Failure Analysis ◽  
Failure Criterion ◽  
Composite Structures ◽  
Progressive Failure ◽  
Textile Composite ◽  
Progressive Failure Analysis

Progressive failure analysis of thin-walled composite structures

2013 ◽  
Vol 95 ◽  
pp. 53-62 ◽  
Author(s):  
Diego Cárdenas ◽  
Hugo Elizalde ◽  
Piergiovanni Marzocca ◽  
Frank Abdi ◽  
Levon Minnetyan ◽  
...  
Keyword(s):  
Failure Analysis ◽  
Composite Structures ◽  
Progressive Failure ◽  
Progressive Failure Analysis ◽  
Thin Walled

scholarly journals Development and Evaluation of Crack Band Model Implemented Progressive Failure Analysis Method for Notched Composite Laminate

2019 ◽  
Vol 9 (24) ◽  
pp. 5572
Author(s):  
Donghyun Yoon ◽  
Sangdeok Kim ◽  
Jaehoon Kim ◽  
Youngdae Doh
Keyword(s):  
Failure Analysis ◽  
Failure Criterion ◽  
Composite Laminate ◽  
Progressive Failure ◽  
Numerical Results ◽  
Band Model ◽  
Failure Initiation ◽  
Progressive Failure Analysis ◽  
Crack Band ◽  
Tension And Compression

Progressive failure analysis (PFA) is widely used to predict the failure behavior of composite materials. As a structure becomes more complex with discontinuities, prediction of failure becomes more difficult and mesh dependence must be taken into account. In this study, a PFA model was developed using the Hashin failure criterion and crack band model. The failure initiation was evaluated using the Hashin failure criterion. If failure initiation occurred, the damage variables at each failure mode (fiber tension and compression; matrix tension and compression) were calculated according to linear softening degradation and they were then used to derive the damaged stiffness matrix. This matrix reflected a degraded material, and PFA was continued until the damage variables became “1,” implying complete material failure. A series of processes were performed using the finite element method program ABAQUS with a user-defined material subroutine. To evaluate the proposed PFA model, experimental results of open-hole composite laminate tests were compared with the obtained numerical results. The strain behaviors were compared using a digital image correlation system. The obtained numerical results were in good agreement with the experimental ones.

Failure Analysis of Laminated Composites under in-Plane Compressive Loading

2012 ◽  
Vol 476-478 ◽  
pp. 583-586
Author(s):  
Yin Huan Yang
Keyword(s):  
Failure Analysis ◽  
Composite Laminates ◽  
Composite Structures ◽  
Parametric Design ◽  
Laminated Composites ◽  
Progressive Failure ◽  
Compressive Loading ◽  
Laminated Composite ◽  
Progressive Failure Analysis ◽  
Ultimate Failure

Failure prediction of laminated composites is performed by progressive failure analysis method. A modified form of Hashin’s failure criterion by Shokrieh is used to detect the failure, where a sudden degradation model is proposed to reduce engineering material constants. The numerical analysis of composite laminates is implemented in ANSYS Parametric Design Language (APDL) with commercial finite element codes ANSYS. The method can predict the initiation and propagation of local damage and response of laminated composite structures from initial loading and ultimate failure. The model has been validated by comparing numerical results with existing experimental results. And then failure analysis specimen fabricated from M40J/Ag80 and investigation on influence of stacking sequences and fiber orientations under in-plane compressive loading have been performed by the proposed model.

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