基于剩余壽命的金屬板-復合材料膠接修補優(yōu)化設計.pdf

1、南京航空航天大學碩士學位論文基于剩余壽命的金屬板復合材料膠接修補優(yōu)化設計姓名：侯成莉申請學位級別：碩士專業(yè)：飛行器設計指導教師：沈海軍201103基于剩余疲勞壽命的金屬板復合材料膠接修補優(yōu)化設計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