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A simple analysis method based upon a transverse shear deformation theory and a sublaminate approach is utilized to analyze a mixed-mode edge delamination specimen. The analysis provides closed form expressions for the interlaminar shear stresses ahead of the crack, the total strain energy release rate, and the strain energy release rate components. The parameters controlling the behavior are identified. The effect of specimen stacking sequence and delamination interface on the strain energy release rate components is investigated. Results are compared with a finite element simulation for reference. The simple nature of the method makes it suitable for preliminary design analyses which require a large number of configurations to be evaluated quickly and economically.
In Part I of this work the analytical model is developed. A comparison of the characteristic roots controlling the behavior in the edge delamination specimen is provided. In Part II an extensive comparison with a finite element solution for 58 test cases is provided in order to validate the analytical model and assess its accuracy.
Assistant professor, School of Aerospace Engineering, Georgia Institute of Technology, Atlanta, GA
Professor, University of California, Davis, CA
Stock #: CTR10166J