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1、COMPOSITESTRUCTURESELSEVIERCompositeStructures42(1998)13-21PostbucklingandfailureofstiffenedcompositepanelsunderaxialcompressionCheo!-WonKong,In-CheolLee,Chun-GonKim,Chang-SunHong*DepurtmentofAerospaceEngineering,KoreaAdvancedInstituteofScienceandTechnology,373-1,Kusong-dong,Yuso
2、ng-gu,Teajon305-701,KoreaAbstractThepostbucklingbehaviorofgraphite-epoxylaminatedstiffenedpanelshasbeenstudiedanalyticallyandexperimentallyherein.Inthisresearch,thestiffenedpanelswereanalyzedusingthenonlinearfiniteelementmethod.Theprogressivefailureanalysisadoptedthemaximumstress
3、criterionandthecompleteunloadingfailuremodel.Inthefailureanalysis,theconsideredfailuremodeswerematrixfailure,shearfailureandfiberfailure.Thestiffenerswereformedbythecontinuouslay-upoftheskintoimprovetheintegrityofthestiffenedcompositepanels.AshadowmoirCtechniquewasusedtomonitorth
4、eout-of-planedeformationoftheskinpanel.Piezoelectricfilmsensorswereusedtodetectthefailureeventsduringexperiments.Theanalyticalresultsonthebucklingload,postbucklingbehavior,andpostbucklingcompressivestrengthshowedgoodagreementwiththeexperimentalresults.Parametricstudieswereconduct
5、edtoshowtheeffectsofstackingsequencesandstiffenershapesonthebucklingloadandpostbucklingcompressivestrengthofstiffenedcompositepanels.01998PublishedbyElsevierScienceLtd.Allrightsreserved.1.Introductionsitepanelsbyfiniteelementmethodwitharc-lengthcontrol[lo].Chattopadhyayanalyzedst
6、iffenedcompo-Compositematerialssuchasgraphite-epoxyaresitepanelsconsideringlargedeflections[ll].Mostusedinspacevehicles,missilesandaircraft.Thepreviouspapersdidnotinvestigatepostbucklingbehav-graphite-epoxylaminatedstiffenedpanelsareexten-iorswithrespecttocompressivestrength.sive
7、lyusedinaircraftstructuralcomponentstosatisfyInthepresentstudy,stiffenedcompositepanelswererequirementsofincreasedstiffnessandreducedweight.fabricatedbycuringthestiffenerswiththeskininaThedesignofthestiffenedpanelsisbasedoncontinuouslaminate.Thetwotypesofstiffeners,bladepostbuckl
8、ingcompressivestrengthwithconsiderationa
