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An impacted region of a composite laminated plate is characterized by elliptical ply delamination around a central region of smashed fibers. Delamination occurs through the thickness and increases in size towards the back surface. The loading case that will most easily cause failure of the plate is compressive loading in which case a delaminated section buckles. This gives rise to global buckling of the plate or extensive delamination and fatal loss of residual strength.
A representative model of an impacted region is a circular sublaminate with a central hole. A closed-form stability analysis for the case of uniaxial compressive loading has been performed on the model. The critical buckling strains are found to conform to a law analogous to that of classical plate buckling, and a strong sensitivity to the radius of the central hole and ply layup of the delaminated section is observed.
Staff scientist, Lockheed Aeronautical Systems Company, Burbank, CA
Senior research and development engineer, Lockheed Aeronautical Systems Company, Burbank, CA
Visiting scientist, Lockheed International Research Institute, Burbank, CA
Stock #: CTR10137J