{"title":"超音速运输机复合材料翼板疲劳损伤累积的数值研究","authors":"N. V. Turbin, K. A. Shelkov","doi":"10.1007/s42401-023-00200-1","DOIUrl":null,"url":null,"abstract":"<div><p>In this paper, the patterns of fatigue damage accumulation for a stringer panel and a panel with lattice reinforcement made of a polymer composite material (PCM) were studied using the Wim Van Paepegem calculation method. Both panels have the same overall dimensions, are made of the same material and are designed to carry the same compressive load. Based on the results of the calculations, the zones were determined in which the greatest loss of stiffness occurs in one of the components for both types of panels. The number of cycles to complete loss of stiffness for these components for each of the zones was obtained. It was found that in the stringer panel, the greatest loss of stiffness occurs in the layers of the stringer web and in the panel with lattice reinforcement in the zone where the diagonal ribs intersect. At the same time, it was found that in a lattice panel, these fatigue damage occurs under a smaller number of applied cycles than in a stringer panel.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":null,"pages":null},"PeriodicalIF":0.0000,"publicationDate":"2023-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":"{\"title\":\"Numerical study of fatigue damage accumulation in composite wing panels of prospective supersonic transport aircraft\",\"authors\":\"N. V. Turbin, K. A. Shelkov\",\"doi\":\"10.1007/s42401-023-00200-1\",\"DOIUrl\":null,\"url\":null,\"abstract\":\"<div><p>In this paper, the patterns of fatigue damage accumulation for a stringer panel and a panel with lattice reinforcement made of a polymer composite material (PCM) were studied using the Wim Van Paepegem calculation method. Both panels have the same overall dimensions, are made of the same material and are designed to carry the same compressive load. Based on the results of the calculations, the zones were determined in which the greatest loss of stiffness occurs in one of the components for both types of panels. The number of cycles to complete loss of stiffness for these components for each of the zones was obtained. It was found that in the stringer panel, the greatest loss of stiffness occurs in the layers of the stringer web and in the panel with lattice reinforcement in the zone where the diagonal ribs intersect. At the same time, it was found that in a lattice panel, these fatigue damage occurs under a smaller number of applied cycles than in a stringer panel.</p></div>\",\"PeriodicalId\":36309,\"journal\":{\"name\":\"Aerospace Systems\",\"volume\":null,\"pages\":null},\"PeriodicalIF\":0.0000,\"publicationDate\":\"2023-03-01\",\"publicationTypes\":\"Journal Article\",\"fieldsOfStudy\":null,\"isOpenAccess\":false,\"openAccessPdf\":\"\",\"citationCount\":\"0\",\"resultStr\":null,\"platform\":\"Semanticscholar\",\"paperid\":null,\"PeriodicalName\":\"Aerospace Systems\",\"FirstCategoryId\":\"1085\",\"ListUrlMain\":\"https://link.springer.com/article/10.1007/s42401-023-00200-1\",\"RegionNum\":0,\"RegionCategory\":null,\"ArticlePicture\":[],\"TitleCN\":null,\"AbstractTextCN\":null,\"PMCID\":null,\"EPubDate\":\"\",\"PubModel\":\"\",\"JCR\":\"Q3\",\"JCRName\":\"Earth and Planetary Sciences\",\"Score\":null,\"Total\":0}","platform":"Semanticscholar","paperid":null,"PeriodicalName":"Aerospace Systems","FirstCategoryId":"1085","ListUrlMain":"https://link.springer.com/article/10.1007/s42401-023-00200-1","RegionNum":0,"RegionCategory":null,"ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"Q3","JCRName":"Earth and Planetary Sciences","Score":null,"Total":0}
Numerical study of fatigue damage accumulation in composite wing panels of prospective supersonic transport aircraft
In this paper, the patterns of fatigue damage accumulation for a stringer panel and a panel with lattice reinforcement made of a polymer composite material (PCM) were studied using the Wim Van Paepegem calculation method. Both panels have the same overall dimensions, are made of the same material and are designed to carry the same compressive load. Based on the results of the calculations, the zones were determined in which the greatest loss of stiffness occurs in one of the components for both types of panels. The number of cycles to complete loss of stiffness for these components for each of the zones was obtained. It was found that in the stringer panel, the greatest loss of stiffness occurs in the layers of the stringer web and in the panel with lattice reinforcement in the zone where the diagonal ribs intersect. At the same time, it was found that in a lattice panel, these fatigue damage occurs under a smaller number of applied cycles than in a stringer panel.
期刊介绍：
Aerospace Systems provides an international, peer-reviewed forum which focuses on system-level research and development regarding aeronautics and astronautics. The journal emphasizes the unique role and increasing importance of informatics on aerospace. It fills a gap in current publishing coverage from outer space vehicles to atmospheric vehicles by highlighting interdisciplinary science, technology and engineering.
Potential topics include, but are not limited to:
Trans-space vehicle systems design and integration
Air vehicle systems
Space vehicle systems
Near-space vehicle systems
Aerospace robotics and unmanned system
Communication, navigation and surveillance
Aerodynamics and aircraft design
Dynamics and control
Aerospace propulsion
Avionics system
Opto-electronic system
Air traffic management
Earth observation
Deep space exploration
Bionic micro-aircraft/spacecraft
Intelligent sensing and Information fusion
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