{"title":"复合材料加筋板在冲击作用下的损伤容限尺寸","authors":"H. Dalir","doi":"10.1109/ICMAE.2016.7549510","DOIUrl":null,"url":null,"abstract":"The design of aircraft composite stiffened structures subjected to dynamic and impact loadings requires several experimental testing scenarios on the full-size structure. The present paper deals with investigating the feasibility of the use of sub-size test specimens under vertical and lateral impacts on the stiffener free flange based on finite element (FE) models. Simulations were performed on sub-size specimens carefully extracted from the full-size (26.4 × 48.4 × 2.4 in3) impact test panels. The main required specifications of an in-house falling weight impact tester were also determined, discussing the required fixture/jig configuration.","PeriodicalId":371629,"journal":{"name":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"20 1","pages":"0"},"PeriodicalIF":0.0000,"publicationDate":"2016-07-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":"{\"title\":\"Damage tolerance coupon sizing of composite stiffened panels under impact\",\"authors\":\"H. Dalir\",\"doi\":\"10.1109/ICMAE.2016.7549510\",\"DOIUrl\":null,\"url\":null,\"abstract\":\"The design of aircraft composite stiffened structures subjected to dynamic and impact loadings requires several experimental testing scenarios on the full-size structure. The present paper deals with investigating the feasibility of the use of sub-size test specimens under vertical and lateral impacts on the stiffener free flange based on finite element (FE) models. Simulations were performed on sub-size specimens carefully extracted from the full-size (26.4 × 48.4 × 2.4 in3) impact test panels. The main required specifications of an in-house falling weight impact tester were also determined, discussing the required fixture/jig configuration.\",\"PeriodicalId\":371629,\"journal\":{\"name\":\"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)\",\"volume\":\"20 1\",\"pages\":\"0\"},\"PeriodicalIF\":0.0000,\"publicationDate\":\"2016-07-18\",\"publicationTypes\":\"Journal Article\",\"fieldsOfStudy\":null,\"isOpenAccess\":false,\"openAccessPdf\":\"\",\"citationCount\":\"0\",\"resultStr\":null,\"platform\":\"Semanticscholar\",\"paperid\":null,\"PeriodicalName\":\"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)\",\"FirstCategoryId\":\"1085\",\"ListUrlMain\":\"https://doi.org/10.1109/ICMAE.2016.7549510\",\"RegionNum\":0,\"RegionCategory\":null,\"ArticlePicture\":[],\"TitleCN\":null,\"AbstractTextCN\":null,\"PMCID\":null,\"EPubDate\":\"\",\"PubModel\":\"\",\"JCR\":\"\",\"JCRName\":\"\",\"Score\":null,\"Total\":0}","platform":"Semanticscholar","paperid":null,"PeriodicalName":"2016 7th International Conference on Mechanical and Aerospace Engineering (ICMAE)","FirstCategoryId":"1085","ListUrlMain":"https://doi.org/10.1109/ICMAE.2016.7549510","RegionNum":0,"RegionCategory":null,"ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"","JCRName":"","Score":null,"Total":0}
Damage tolerance coupon sizing of composite stiffened panels under impact
The design of aircraft composite stiffened structures subjected to dynamic and impact loadings requires several experimental testing scenarios on the full-size structure. The present paper deals with investigating the feasibility of the use of sub-size test specimens under vertical and lateral impacts on the stiffener free flange based on finite element (FE) models. Simulations were performed on sub-size specimens carefully extracted from the full-size (26.4 × 48.4 × 2.4 in3) impact test panels. The main required specifications of an in-house falling weight impact tester were also determined, discussing the required fixture/jig configuration.
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