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035   $a(EXLCZ)995470000002469465
100   $a20170223j199702    ua             0
101 0 $aeng
135   $aurbn|||||||||
181   $ctxt$2rdacontent
182   $cc$2rdamedia
183   $acr$2rdacarrier
200 10$aCompression response of a sandwich fuselage keel panel with and without damage /$fDavid M. McGowan and Damodar R. Ambur
210  1$aHampton, Virginia :$cNational Aeronautics and Space Administration, Langley Research Center,$dFebruary 1997.
215   $a1 online resource (33 pages) $cillustrations
225 1 $aNASA technical memorandum ;$v110302
300   $a"February 1997."
300   $a"Performing organization: NASA Langley Research Center" Report documentation page.
320   $aIncludes bibliographical references (pages 13-14).
606   $aComposite structures$2nasat
606   $aFinite element method$2nasat
606   $aFuselages$2nasat
606   $aGraphite-epoxy composites$2nasat
606   $aHoneycomb cores$2nasat
606   $aImpact damage$2nasat
606   $aSandwich structures$2nasat
615  7$aComposite structures.
615  7$aFinite element method.
615  7$aFuselages.
615  7$aGraphite-epoxy composites.
615  7$aHoneycomb cores.
615  7$aImpact damage.
615  7$aSandwich structures.
700   $aMcGowan$b David M.$01400479
702   $aAmbur$b Damodar R.
712 02$aLangley Research Center,
801  0$bGPO
801  1$bGPO
906   $aBOOK
912   $a9910707910803321
996   $aCompression response of a sandwich fuselage keel panel with and without damage$93526749
997   $aUNINA