Study of compression-loaded and impact-damaged structurally efficient graphite-thermoplastic trapezoidal-corrugation sandwich and semisandwich panels
Dawn C. Jegley, United States. National Aeronautics and Space Administration. Scientific and Technical Information Program
National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992 - Technology & Engineering - 31 pages
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aircraft aluminum wing aluminum wing compression axial compression axial half-waves Commercial aircraft aluminum Composite Materials control and impact-damaged control panels Corrugation width damage deform out-of-plane deformation pattern deformation shape Deformations at P/PCT end-shortening failed panel failure is shown failure loads finite-element analysis graphite graphite-thermoplastic panels heavily loaded semisandwich impact-damaged panels in/in integral number laminate Langley Research Center lb/in loaded semisandwich panel Loading direction low load levels material properties Moire pattern NASA number of plies of-plane optimal panel designs out-of-plane deformations panel AC Panel Configurations panel failed panel is shown panel length PASCO Poisson's ratios postbuckling prior to failure prior to loading rugation sandwich and semisandwich sandwich panel section of panel section of skin semisand shear stiffness shear strain shown in figure skin and corrugation stacking sequence strain gauges structural efficiency test specimens thermoforming thermoplastic tion trapezoidal-corrugation sandwich weight index W/AL wich panel wing compression panels Young's modulus