{"title":"机翼主梁翼缘疲劳裂纹扩展模拟","authors":"P. Augustin","doi":"10.13164/conf.read.2018.7","DOIUrl":null,"url":null,"abstract":"Simulation of fatigue crack growth in the bottom flange of twin turboprop commuter aircraft wing spar is described in this paper. Analysed crack propagation scenario represents real wing fullscale fatigue test failure. Computational model of bottom flange was prepared using threedimensional fracture mechanics software FRANC3D. Calculation of crack growth under the variable amplitude loading was performed in AFGROW code using the NASGRO equation and Wheeler retardation model. It was verified with the results of wing spar specimen fatigue test and fractograpic analysis of fatigue fracture from this experiment. Computational model was applied in the prognostic algorithm of structure health monitoring system. NOMENCLATURE a crack length da/dN crack growth rate G shear modulus K stress intensity factor KC fracture toughness Kop opening stress intensity factor Kth threshold stress intensity factor range R stress ratio constraint factor Poisson’s ratio O flow stress YS tensile yield strength","PeriodicalId":340623,"journal":{"name":"13th Research and Education in Aircraft Design: Conference proceedings","volume":"24 1","pages":"0"},"PeriodicalIF":0.0000,"publicationDate":"1900-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":"{\"title\":\"Simulation of fatigue crack propagation in the wing main spar flange\",\"authors\":\"P. Augustin\",\"doi\":\"10.13164/conf.read.2018.7\",\"DOIUrl\":null,\"url\":null,\"abstract\":\"Simulation of fatigue crack growth in the bottom flange of twin turboprop commuter aircraft wing spar is described in this paper. Analysed crack propagation scenario represents real wing fullscale fatigue test failure. Computational model of bottom flange was prepared using threedimensional fracture mechanics software FRANC3D. Calculation of crack growth under the variable amplitude loading was performed in AFGROW code using the NASGRO equation and Wheeler retardation model. It was verified with the results of wing spar specimen fatigue test and fractograpic analysis of fatigue fracture from this experiment. Computational model was applied in the prognostic algorithm of structure health monitoring system. NOMENCLATURE a crack length da/dN crack growth rate G shear modulus K stress intensity factor KC fracture toughness Kop opening stress intensity factor Kth threshold stress intensity factor range R stress ratio constraint factor Poisson’s ratio O flow stress YS tensile yield strength\",\"PeriodicalId\":340623,\"journal\":{\"name\":\"13th Research and Education in Aircraft Design: Conference proceedings\",\"volume\":\"24 1\",\"pages\":\"0\"},\"PeriodicalIF\":0.0000,\"publicationDate\":\"1900-01-01\",\"publicationTypes\":\"Journal Article\",\"fieldsOfStudy\":null,\"isOpenAccess\":false,\"openAccessPdf\":\"\",\"citationCount\":\"0\",\"resultStr\":null,\"platform\":\"Semanticscholar\",\"paperid\":null,\"PeriodicalName\":\"13th Research and Education in Aircraft Design: Conference proceedings\",\"FirstCategoryId\":\"1085\",\"ListUrlMain\":\"https://doi.org/10.13164/conf.read.2018.7\",\"RegionNum\":0,\"RegionCategory\":null,\"ArticlePicture\":[],\"TitleCN\":null,\"AbstractTextCN\":null,\"PMCID\":null,\"EPubDate\":\"\",\"PubModel\":\"\",\"JCR\":\"\",\"JCRName\":\"\",\"Score\":null,\"Total\":0}","platform":"Semanticscholar","paperid":null,"PeriodicalName":"13th Research and Education in Aircraft Design: Conference proceedings","FirstCategoryId":"1085","ListUrlMain":"https://doi.org/10.13164/conf.read.2018.7","RegionNum":0,"RegionCategory":null,"ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"","JCRName":"","Score":null,"Total":0}
Simulation of fatigue crack propagation in the wing main spar flange
Simulation of fatigue crack growth in the bottom flange of twin turboprop commuter aircraft wing spar is described in this paper. Analysed crack propagation scenario represents real wing fullscale fatigue test failure. Computational model of bottom flange was prepared using threedimensional fracture mechanics software FRANC3D. Calculation of crack growth under the variable amplitude loading was performed in AFGROW code using the NASGRO equation and Wheeler retardation model. It was verified with the results of wing spar specimen fatigue test and fractograpic analysis of fatigue fracture from this experiment. Computational model was applied in the prognostic algorithm of structure health monitoring system. NOMENCLATURE a crack length da/dN crack growth rate G shear modulus K stress intensity factor KC fracture toughness Kop opening stress intensity factor Kth threshold stress intensity factor range R stress ratio constraint factor Poisson’s ratio O flow stress YS tensile yield strength
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