Intra-inter Crack Band Model (I2CBM) for Progressive Damage and Failure Analysis of Joints

2017 ◽  
Author(s):  
Ashith P K Joseph ◽  
Paul Davidson ◽  
Anthony M. Waas
Keyword(s):  
Failure Analysis ◽  
Band Model ◽  
Progressive Damage ◽  
Damage And Failure ◽  
Crack Band

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.

Structures Technology for Component Damage and Failure Prediction

2021 ◽  
Author(s):  
Yuri Nikishkov ◽  
Gennadiy Nikishkov ◽  
Guillaume Seon ◽  
Brian Shonkwiler ◽  
Andrew Makeev ◽  
...  
Keyword(s):  
Failure Analysis ◽  
Failure Modes ◽  
A Priori ◽  
Structural Features ◽  
Advanced Materials ◽  
Life Extension ◽  
Repeated Loading ◽  
Progressive Damage ◽  
Damage And Failure ◽  
Composite Tape

Advanced structural analysis methods, known as progressive damage and failure analysis tools, are being developed to predict initiation and propagation of damage under repeated loading based on capturing individual and interacting damage modes. This work shows the ability of the progressive damage and failure analysis method implemented in CDMat software developed at the University of Texas Arlington Advanced Materials and Structures Lab to predict strength and fatigue failure of an advanced mechanically fastened aerospace structural joint, the common feature test component (CFTC)—representative of flight-critical structural attributes and failure modes—without a priori knowledge of the test result. The CFTC structural features include a composite tape skin, a composite fabric stiffener, and an aluminum rib applying pull-through load through multiple countersunk bolts combined with the axial compression of skin and stiffener. Failure and damage predictions under static and constant-amplitude cyclic loading are compared with tests. Developed by Boeing under the Air Force Research Laboratory Composite Airframe Life Extension Program, the CFTC has been the most complex progressive damage and failure analysis validation article to date.

Benchmarking Mixed Mode Matrix Failure in Progressive Damage and Failure Analysis Methods

2018 ◽  
Author(s):  
FRANK LEONE ◽  
MADHAVADAS RAMNATH ◽  
IMRAN HYDER ◽  
STEVEN WANTHAL ◽  
JOSEPH SCHAEFER ◽  
...  
Keyword(s):  
Failure Analysis ◽  
Mixed Mode ◽  
Progressive Damage ◽  
Damage And Failure ◽  
Analysis Methods

Micromechanical Progressive Failure Analysis of Fiber-Reinforced Composite Using Refined Beam Models

2017 ◽  
Vol 85 (2) ◽  
Author(s):  
I. Kaleel ◽  
M. Petrolo ◽  
A. M. Waas ◽  
E. Carrera
Keyword(s):  
Failure Analysis ◽  
Progressive Failure ◽  
Computational Cost ◽  
Band Model ◽  
Beam Model ◽  
Fiber Reinforced ◽  
Band Theory ◽  
Progressive Failure Analysis ◽  
Crack Band ◽  
The Matrix

An efficient and novel micromechanical computational platform for progressive failure analysis of fiber-reinforced composites is presented. The numerical framework is based on a recently developed micromechanical platform built using a class of refined beam models called Carrera unified formulation (CUF), a generalized hierarchical formulation which yields a refined structural theory via variable kinematic description. The crack band theory is implemented in the framework to capture the damage propagation within the constituents of composite materials. The initiation and orientation of the crack band in the matrix are determined using the maximum principal stress state and the traction-separation law governing the crack band growth is related to the fracture toughness of the matrix. A representative volume element (RVE) containing randomly distributed fibers is modeled using the component-wise (CW) approach, an extension of CUF beam model based on Lagrange type polynomials. The efficiency of the proposed numerical framework is achieved through the ability of the CUF models to provide accurate three-dimensional (3D) displacement and stress fields at a reduced computational cost. The numerical results are compared against experimental data available in the literature and an analogous 3D finite element model with the same constitutive crack band model. The applicability of CUF beam models as a novel micromechanical platform for progressive failure analysis as well as the multifold efficiency of CUF models in terms of CPU time are highlighted.

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