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A validation of the sublaminate analysis method developed earlier is provided in this work by comparison of the predictions with a quasi-three-dimensional finite element analysis. A comparison of the total strain energy release rate with a classical plate model is also provided. Closed-form expressions for the total strain energy rate and the strain energy release rate components are developed. The sublaminate analysis developed in this work is simple and the results are generated using a desktop computer.
Assistant professor, Georgia Institute of Technology, School of Aerospace Engineering, Atlanta, GA
Senior scientist, Analytical Services and Materials, Inc., Hampton, VA
Professor, University of California, Davis, CA
Senior scientist, U.S. Army Aerostructures Directorate, NASA Langley Research Center, Hampton, VA
Stock #: CTR10167J