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1、【叶片结构设计工程师,国电联合动力技术有限公司】前程无忧官方招聘网站Theseloadscancausedamageorweakeningofthestructureespeciallyforagingmilitaryandcivilianaircrafttherebyaffectingitsloadcarryingcapabilities.Hence,arepairorreinforcementofthedamagedorweakenedpartofthestructuretorestorethestructuralefficiencyandth

2、usassurethecontinuedairworthinessoftheaircrafthasbecomeanimportantissueinrecentyearstomilitaryandcivilianaircraftoperators.TheUSAirForceinrecentyearshasshownconsiderableinterestintheuseofadvancedcompositestorepaircrackedmetallicaircraftstructurestoenhancetheirlife.Oneissueprev

3、entingusingbondedcompositepatches,asastandardmeansofrepairingdamagedmetallicaircraftstructuresisthefactthattheintegrityoftherepairsisunknown.Inthispaperthedesign,analysisanddurabilityofadhesivelybondedcompositepatchrepairsofcrackedaircraftaluminumpanelsisreported.Pre-cracked20

4、24-T3cladaluminumpanelsof381×89×1.6mm(15×3.5×0.063in.)repairedwithoctagonalsinglesidedboron/epoxycompositepatchwereusedastestspecimen.Twodifferentcompositeplyconfigurations,5-and6-plywereinvestigated.Linearandnon-linearfiniteelementanalyseswereperformedonthetestspecimenusing8-

5、noded24degreeoffreedom(DOF)hexagonalelementsforthealuminumpanel,boron/epoxypatchandadhesivematerialsubjectedtouni-axialtensileloading.Thestressdistributionsobtainedwereusedtopredicttheincreaseinstrengthanddurabilityoftherepairedstructure.Acomparisonofthestressvaluesatcriticalp

6、ointswasmade.Theanalysisalsowasusedtovalidatevariousassumptionsmadeinthedesignofthecompositepatch.Experimentalinvestigationswereconductedonthecrackedaluminumpanelrepairedwitha5-plycompositepatchaswellasontwobaseline-unpatchedpanels(onewithacrackandonewithnocrack)byuni-axialten

7、siletestingtovalidatetheanalyticalresults.TheexperimentwasconductedontheInstrontension-testingmachine.Itwasfoundthatthemaximumskinstressdecreasessignificantlyaftertheapplicationofthepatchandtheregionofmaximumskinstressshiftsfromthecrackfrontforanunpatchedpaneltothepatchedgesfo

8、rapatchedone.ArticleOutline1.Introduction2.Problemdefinition3