Strain energy release rate analysis of adhesive-bonded composite joints with a prescribed interlaminar crack
Chadegani, Alireza Yang, Chihdar Charles Dan-Jumbo, Eugene
Chadegani, Alireza
Yang, Chihdar Charles
Dan-Jumbo, Eugene
Other Names
Location
Time Period
Advisors
Original Date
Digitization Date
Issue Date
2009-01
Type
Article
Genre
Keywords
Finite element method,Boundary conditions,Composite structures,Crack closure,Crack propagation,Cracks,Difference equations,Dynamics,Energy release rate,Failure analysis,Fiber optics,Image segmentation,Joints (structural components),Laminated composites,Laminating,Quality assurance,Reliability,Standardization,Standards,Strain energy,Strain rate,Stress concentration,Stresses,Structural dynamics,Structure (composition)
Subjects (LCSH)
Citation
Chadegani, A., Yang, C., & Dan-Jumbo, E. (2008). Strain energy release rate analysis of adhesive-bonded composite joints with a prescribed interlaminar crack. Paper presented at the Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
Abstract
Delamination is among the critical failure modes in fiber-reinforced laminated composite structures. This paper presents an analytical approach by taking into account the first-ply failure in adhesive-bonded composite joints subjected to axial tension. The ASTM D3165 standard test specimen geometry is followed for model development derivations. The field equations, in terms of displacements within the joint, are formulated by using the first-order, shear-deformable, laminated plate theory together with kinematics relations and force equilibrium conditions. The stress distributions for the adherends and adhesive are determined after the appropriate boundary and loading conditions are applied and the equations for the field displacements are solved. The equivalent forces at the tip of the prescribed interlaminar crack are obtained based on interlaminar stress distributions. The strain energy release rate of the crack is then determined by using the virtual crack closure technique (VCCT). The system of second-order differential field equations is solved to provide the adherend and adhesive stresses using the symbolic computation tool, Maple 9.52. Finite element analyses using the J-integral as well as the VCCT are performed to verify the developed analytical model. Finite element analyses are conducted using the commercial finite element analysis software ABAQUS 6.5-1. Results are determined using the analytical method correlated properly with the results from the finite element analyses.
Table of Contents
Description
Click on the DOI link to access the article (may not be free).
Publisher
American Institute of Aeronautics and Astronautics
Journal
Book Title
Series
Journal of Aircraft
v.46 no.1
v.46 no.1
Digital Collection
Finding Aid URL
Use and Reproduction
Archival Collection
PubMed ID
DOI
ISSN
0021-8669
1533-3868 (online)
1533-3868 (online)