LEADER 01995nam  2200565I  450 
001 9910705871503321
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035   $a(CKB)5470000002453700
035   $a(OCoLC)994642614
035   $a(EXLCZ)995470000002453700
100   $a20170725j199806    ua             0
101 0 $aeng
135   $aurbn|||||||||
181   $ctxt$2rdacontent
182   $cc$2rdamedia
183   $acr$2rdacarrier
200 12$aA progressive damage methodology for residual strength predictions of notched composite panels /$fTimothy W. Coats and Charles E. Harris
210  1$aHampton, Virginia :$cNational Aeronautics and Space Administration, Langley Research Center,$dJune 1998.
215   $a1 online resource (43 pages) $cillustrations
225 1 $aNASA/TM ;$v1998-207646
300   $a"June 1998."
300   $a"Performing organization: NASA Langley Research Center"--Report documentation page.
320   $aIncludes bibliographical references (pages 22-24).
606   $aComposite structures$2nasat
606   $aCrack propagation$2nasat
606   $aEpoxy matrix composites$2nasat
606   $aFractography$2nasat
606   $aFracture mechanics$2nasat
606   $aFracture strength$2nasat
606   $aLaminates$2nasat
606   $aLoads (forces)$2nasat
606   $aResidual strength$2nasat
615  7$aComposite structures.
615  7$aCrack propagation.
615  7$aEpoxy matrix composites.
615  7$aFractography.
615  7$aFracture mechanics.
615  7$aFracture strength.
615  7$aLaminates.
615  7$aLoads (forces)
615  7$aResidual strength.
700   $aCoats$b Timothy W.$01397146
702   $aHarris$b Charles E.$f1950-
712 02$aLangley Research Center,
801  0$bGPO
801  1$bGPO
906   $aBOOK
912   $a9910705871503321
996   $aA progressive damage methodology for residual strength predictions of notched composite panels$93458432
997   $aUNINA