01841nam 2200517I 450 991070791080332120170322081517.0(CKB)5470000002469465(OCoLC)973554536(EXLCZ)99547000000246946520170223j199702 ua 0engurbn|||||||||txtrdacontentcrdamediacrrdacarrierCompression response of a sandwich fuselage keel panel with and without damage /David M. McGowan and Damodar R. AmburHampton, Virginia :National Aeronautics and Space Administration, Langley Research Center,February 1997.1 online resource (33 pages) illustrationsNASA technical memorandum ;110302"February 1997.""Performing organization: NASA Langley Research Center" Report documentation page.Includes bibliographical references (pages 13-14).Composite structuresnasatFinite element methodnasatFuselagesnasatGraphite-epoxy compositesnasatHoneycomb coresnasatImpact damagenasatSandwich structuresnasatComposite structures.Finite element method.Fuselages.Graphite-epoxy composites.Honeycomb cores.Impact damage.Sandwich structures.McGowan David M.1400479Ambur Damodar R.Langley Research Center,GPOGPOBOOK9910707910803321Compression response of a sandwich fuselage keel panel with and without damage3526749UNINA