Stiffness properties of composite laminates with matrix cracking and interior delamination

1986 ◽  
Vol 25 (5-6) ◽  
pp. 751-762 ◽  
Author(s):  
Ramesh Talreja
Keyword(s):  
Composite Laminates ◽  
Matrix Cracking ◽  
Stiffness Properties

Analysis of Fatigue Damage Mechanisms and Residual Properties of Polymer Matrix Composites

2000 ◽  
Author(s):  
Costas Soutis ◽  
Maria Kashtalyan
Keyword(s):  
Composite Laminates ◽  
Polymer Matrix Composites ◽  
Matrix Cracking ◽  
Matrix Composites ◽  
Residual Properties ◽  
Stiffness Properties ◽  
Observed Damage ◽  
Equivalent Constraint Model ◽  
Constraint Model ◽  
Longitudinal Cracks

Abstract Resin dominated damage modes such as matrix cracking in the off-axis plies and matrix crack-induced local and edge delaminations are common failure mechanisms in composite laminates under tensile or thermal fatigue. Accurate prediction of the laminate stiffness and strength must consider all the above-mentioned damage modes. In the present paper, an approach is developed for the analysis of cross-ply laminates damaged by transverse and longitudinal cracks and transverse and longitudinal delaminations that initiate and grow along these cracks. It is based on the Equivalent Constraint Model (ECM) of the damaged ply and employs an improved 2-D shear lag method to determine the stress field in the cracked and locally delaminated ply. The method is applied to predict residual stiffness properties of cross-ply graphite/epoxy laminates using experimentally observed damage patterns.

scholarly journals Progressive Matrix Cracking in Composite Laminates Loaded in Tension

1992 ◽  
Vol 1 (1) ◽  
pp. 096369359200100 ◽  
Author(s):  
J Zhang ◽  
J Fan ◽  
C Soutis
Keyword(s):  
Experimental Data ◽  
Theoretical Model ◽  
Crack Initiation ◽  
Composite Laminates ◽  
Matrix Cracking ◽  
Shear Lag ◽  
Simple Theoretical Model ◽  
Stiffness Properties ◽  
Progressive Matrix ◽  
Good Agreement

The reduction of stiffness properties due to transverse ply cracking in [μθ m/90 n] s laminates loaded in quasi-tension is examined theoretically. Predictions of a simple theoretical model based on a modified 2-D shear-lag analysis, are in good agreement with experimental data. The energy released as a result of matrix cracking is also calculated and used to predict crack initiation and multiplication.

scholarly journals Effect of high temperature on the stiffness properties of cracked composite laminates with different off-axis angles

2020 ◽  
Vol 28 ◽  
pp. 864-872
Author(s):  
Mohamed Khodjet Kesba ◽  
A. Benkhedda ◽  
E.A. Adda bedia ◽  
B. Boukert
Keyword(s):  
High Temperature ◽  
Composite Laminates ◽  
Stiffness Properties

Numerical Investigation of a Stiffened Panel Subjected to Low Velocity Impacts

2015 ◽  
Vol 665 ◽  
pp. 277-280 ◽  
Author(s):  
Aniello Riccio ◽  
S. Saputo ◽  
A. Sellitto ◽  
A. Raimondo ◽  
R. Ricchiuto
Keyword(s):  
Numerical Investigation ◽  
Composite Laminates ◽  
Mechanical Response ◽  
Numerical Study ◽  
Fem Analysis ◽  
Matrix Cracking ◽  
Stiffened Panel ◽  
Low Velocity ◽  
Formation And Evolution ◽  
The Impact

The investigation of fiber-reinforced composite laminates mechanical response under impact loads can be very difficult due to simultaneous failure phenomena. Indeed, as a consequence of low velocity impacts, intra-laminar damage as fiber and matrix cracking and inter-laminar damage, such as delamination, often take place concurrently, leading to significant reductions in terms of strength and stability for composite structure. In this paper a numerical study is proposed which, by means of non-linear explicit FEM analysis, aims to completely characterize the composite reinforced laminates damage under low velocity impacts. The numerical investigation allowed to obtain an exhaustive insight on the different phases of the impact event considering the damage formation and evolution. Five different impact locations with the same impact energy are taken into account to investigate the influence on the onset and growth of damage.

scholarly journals Modelling Strategies for Simulating Delamination and Matrix Cracking in Composite Laminates

2014 ◽  
Vol 22 (4) ◽  
pp. 377-403 ◽  
Author(s):  
Frederic Lachaud ◽  
Christine Espinosa ◽  
Laurent Michel ◽  
Pierre Rahme ◽  
Robert Piquet
Keyword(s):  
Composite Laminates ◽  
Matrix Cracking ◽  
Modelling Strategies

Reliability Analysis of Ceramic Matrix Composite Laminates

1993 ◽  
Vol 115 (1) ◽  
pp. 117-121 ◽  
Author(s):  
D. J. Thomas ◽  
R. C. Wetherhold
Keyword(s):  
Composite Laminates ◽  
Ceramic Matrix Composite ◽  
Random Variable ◽  
Ceramic Matrix ◽  
Matrix Cracking ◽  
Bundle Theory ◽  
Fiber Direction ◽  
The Matrix ◽  
Failure Models ◽  
Subsequent Failure

At a macroscopic level, a composite lamina may be considered as a homogeneous orthotropic solid whose directional strengths are random variables. Incorporation of these random variable strengths into failure models, either interactive or noninteractive, allows for the evaluation of the lamina reliability under a given stress state. Using a noninteractive criterion for demonstration purposes, laminate reliabilities are calculated assuming previously established load sharing rules for the redistribution of load as the failure of laminae occurs. The matrix cracking predicted by ACK theory is modeled to allow a loss of stiffness in the fiber direction. The subsequent failure in the fiber direction is controlled by a modified bundle theory. Results using this modified bundle model are compared with previous models, which did not permit separate consideration of matrix cracking, as well as to results obtained from experimental data.

Partial Strain Energy Release Rate for Study Matrix Cracking Evolution in Composite Cross-Ply Laminates

2015 ◽  
Vol 24 (3) ◽  
pp. 096369351502400
Author(s):  
Jean-Luc Rebière
Keyword(s):  
Stress Field ◽  
Composite Laminates ◽  
Strain Energy ◽  
Strain Energy Release Rate ◽  
Strain Energy Release ◽  
Matrix Cracking ◽  
Damage State ◽  
Damage Process ◽  
Cracking Mechanisms ◽  
Observed Damage

Matrix cracking is generally the first observed damage in composite laminates. The stress field distribution in the damaged cross ply laminates is analysed through an approach which uses several hypotheses to simplify the damage state. The proposed cracking criterion involves the respective partial part of the 0° and 90° layers to the damage process. The initiation of transverse and longitudinal cracking mechanisms is predicted.

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