LEADER 01771nam  2200505I  450 
001 9910703784303321
005 20150501110201.0
035   $a(CKB)5470000002433875
035   $a(OCoLC)908252076
035   $a(EXLCZ)995470000002433875
100   $a20150501j198708    ua             0
101 0 $aeng
135   $aurbn|||||||||
181   $ctxt$2rdacontent
182   $cc$2rdamedia
183   $acr$2rdacarrier
200 10$aPostbuckling delamination of a stiffened composite panel using finite element methods /$fS. Natsiavas, C.D. Babcock and W.G. Knauss
210  1$aPasadena, California :$cCalifornia Institute of Technology,$dAugust, 1987.
215   $a1 online resource (9 pages, 10 unnumbered pages) $cillustrations
225 1 $aNASA/CR ;$v182803
300   $aTitle from title screen (viewed May 1, 2015).
300   $a"August, 1987."
300   $a"GALCIT SM report 87-19."
320   $aIncludes bibliographical references (pages 8-9).
606   $aBuckling$2nasat
606   $aDelaminating$2nasat
606   $aFinite element method$2nasat
606   $aCompression loads$2nasat
606   $aPlate theory$2nasat
615  7$aBuckling.
615  7$aDelaminating.
615  7$aFinite element method.
615  7$aCompression loads.
615  7$aPlate theory.
700   $aNatsiavas$b S.$01423118
702   $aBabcock$b Charles D.
702   $aKnauss$b Wolfgang Gustav
712 02$aCalifornia Institute of Technology,
712 02$aUnited States.$bNational Aeronautics and Space Administration,
801  0$bGPO
801  1$bGPO
906   $aBOOK
912   $a9910703784303321
996   $aPostbuckling delamination of a stiffened composite panel using finite element methods$93549549
997   $aUNINA