基于剩余壽命的金屬板-復(fù)合材料膠接修補(bǔ)優(yōu)化設(shè)計(jì).pdf

1、南京航空航天大學(xué)碩士學(xué)位論文基于剩余壽命的金屬板復(fù)合材料膠接修補(bǔ)優(yōu)化設(shè)計(jì)姓名：侯成莉申請(qǐng)學(xué)位級(jí)別：碩士專業(yè)：飛行器設(shè)計(jì)指導(dǎo)教師：沈海軍201103基于剩余疲勞壽命的金屬板復(fù)合材料膠接修補(bǔ)優(yōu)化設(shè)計(jì)IIAbstractThestructuresofcurrentaircraftsaremainlymadeofaluminumalloy.Theaircraftscanoftensuffersomedamagemostofwhicharefat

2、iguecrackstresscrosioncrack..Thedamagedcomponentsmustbereplacedrepairedindertoprolongtheservicelifeofthedamagedaircraftstoensuretheflightsafety.Anewstructuralrepairtechnologyi.e.thetechnologyofrepairingthedamagestructure

3、softheaircraftsbycompositepatcheshasbeendevelopedsincethe1980s.Duetolowweightsmallstressconcentrationlowmaintenancecostmuchlongerlifeoftheadhesivebondedstructuresthetechnologyhasbeenpaidgreatattentionmaderapiddevelopment

4、inmanycountrieswith.Thealuminumalloystructureswidelyusedinaircraftsareinvestigatedinthispaper.Alsotheproblemofrepairingthedamagedmetalplatewithcrackisstudiedbymeansoffiniteelementmethodexperimentalmethod.FirstlytheJamese

5、rsonmethod，i.e.anewexperimentalmethod，isrepresentedtodeterminethestressintensityfact（SIF）oftheLF21aluminumCCT（Centercracktension）platerepairedbycompositepatch.SecondlytherepairedLF21aluminumplatewithcrackisnumericalanaly

6、zedbyfiniteelementmethodthemodificationfactofSIFisobtained.Thentheresultofthemodificationfactiscomparedwiththeexperimentone.Finallytheregularityoftheresidualfatiguelife，fthealuminumalloyplatewithcentralcrack，affectedbyth

7、elengthwidththicknessofthecompositepatchesisstudiedaccdingtothedamagetoleranceview.Meanwhilethedimensionofthecompositepatchesisoptimizedthecriticalsizeisobtainedindertogetthebestrepaireffect.Keywds:Jamesarsonmethodfinite