scholarly journals 3D Progressive Failure Modeling of Drop-Weight Impact on Composite Laminates

2018 ◽  
Author(s):  
DINH CHI PHAM ◽  
JIM LUA ◽  
DIANYUN ZHANG
Keyword(s):  
Composite Laminates ◽  
Progressive Failure ◽  
Failure Modeling ◽  
Drop Weight ◽  
Weight Impact

scholarly journals 3D Progressive Failure Modeling of Drop-Weight Impact on Composite Laminates

2018 ◽  
Author(s):  
DC Pham
Keyword(s):  
Composite Laminates ◽  
Impact Damage ◽  
Progressive Failure ◽  
Damage Model ◽  
Matrix Cracking ◽  
Structural Level ◽  
Velocity Impact ◽  
Drop Weight ◽  
Weight Impact ◽  
The Impact

Composite laminates are susceptible to out-of-plane impact loads due to the lack of reinforcement in the through-thickness direction. Unlike the localized damage induced by a high velocity impact where the incident energy is dissipated near a contact area, low velocity impact damage involves multiple failure mechanisms such as matrix cracking, fiber breakage, and widespread interface delaminations. Depending on the extent of damage, significant reduction in the load-bearing capability of the structure has been observed. The prediction of composite impact damage resistance by a reliable progressive damage analysis tool is essential to reduce intensive and expensive certification tests at structural level. In this work, an enhanced explicit 3D damage model is implemented via VUMAT in Abaqus to perform a drop-weight impact simulation of a [454/04/-454/904]s Hexply AS4/8552 composite laminate. The impact-induced damage and its extent are captured by a 3D Continuum Damage Model (CDM) coupled with an energy driven failure mechanism. The developed module provides a unified solution process for the impact response prediction followed by the residual strength prediction under compression within an explicit solver. Two examples are selected to demonstrate the capability of the progressive failure analysis under dynamic and static loading: 1) a drop-weight test; and 2) an open-hole tension test. Numerical predictions from the developed VUMAT are compared with the test data and predictions using the open source CompDam code developed by NASA.

Simulation of drop-weight impact and compression after impact tests on composite laminates

2012 ◽  
Vol 94 (11) ◽  
pp. 3364-3378 ◽  
Author(s):  
E.V. González ◽  
P. Maimí ◽  
P.P. Camanho ◽  
A. Turon ◽  
J.A. Mayugo
Keyword(s):  
Composite Laminates ◽  
Impact Tests ◽  
Drop Weight ◽  
Compression After Impact ◽  
Weight Impact

Modelling low-speed drop-weight impact on composite laminates

2014 ◽  
Vol 60 ◽  
pp. 520-531 ◽  
Author(s):  
Ang Qiu ◽  
Kunkun Fu ◽  
Wei Lin ◽  
Chengbi Zhao ◽  
Youhong Tang
Keyword(s):  
Composite Laminates ◽  
Low Speed ◽  
Drop Weight ◽  
Weight Impact

scholarly journals Drop weight impact measurements of HE sensitivity: modified detection methods

2014 ◽  
Vol 500 (18) ◽  
pp. 182033 ◽  
Author(s):  
D N Preston ◽  
G W Brown ◽  
B C Tappan ◽  
D M Oshwald ◽  
J R Koby ◽  
...  
Keyword(s):  
Detection Methods ◽  
Drop Weight ◽  
Weight Impact

scholarly journals Progressive Failure Analysis in Open-Hole Tensile Composite Laminates of Airplane Stringers Based on Tests and Simulations

2020 ◽  
Vol 11 (1) ◽  
pp. 185
Author(s):  
Jian Shi ◽  
Mingbo Tong ◽  
Chuwei Zhou ◽  
Congjie Ye ◽  
Xindong Wang
Keyword(s):  
Failure Analysis ◽  
Composite Laminates ◽  
Progressive Failure ◽  
Tensile Load ◽  
Fiber Failure ◽  
Stress Criterion ◽  
Progressive Failure Analysis ◽  
Analysis Technique ◽  
Open Hole ◽  
Failure Types

The failure types and ultimate loads for eight carbon-epoxy laminate specimens with a central circular hole subjected to tensile load were tested experimentally and simulated using two different progressive failure analysis (PFA) methodologies. The first model used a lamina level modeling based on the Hashin criterion and the Camanho stiffness degradation theory to predict the damage of the fiber and matrix. The second model implemented a micromechanical analysis technique coined the generalized method of cells (GMC), where the 3D Tsai–Hill failure criterion was used to govern matrix failure, and the fiber failure was dictated by the maximum stress criterion. The progressive failure methodology was implemented using the UMAT subroutine within the ABAQUS/implicit solver. Results of load versus displacement and failure types from the two different models were compared against experimental data for the open hole laminates subjected to tensile displacement load. The results obtained from the numerical simulation and experiments showed good agreement. Failure paths and accurate damage contours for the tested specimens were also predicted.

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