{"title":"Condition for the Growth of Adhesive Destruction during Cyclic Deformation of Carbon-Fiber Panels","authors":"A. N. Polilov","doi":"10.1134/S1995421224701387","DOIUrl":null,"url":null,"abstract":"<p>Some aspects of the problem of adhesive fracture of aircraft panels made of composite materials under fatigue loading are considered. Algorithms of computer modeling of the delamination development process are described. Various methods of nondestructive testing for identifying the size and location of adhesive failure are analyzed. The cause of adhesion failure between anisotropic layers even under uniaxial tension is explained. The growth of delamination area under cyclic tension is described by an equation in the form of a power-law dependence on the range of the elastic energy release rate. For aircraft panels made of laminated carbon-fiber-reinforced plastics, the independence of the delamination growth rate from its current area is experimentally confirmed.</p>","PeriodicalId":741,"journal":{"name":"Polymer Science, Series D","volume":"17 4","pages":"800 - 808"},"PeriodicalIF":0.5800,"publicationDate":"2025-03-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":null,"platform":"Semanticscholar","paperid":null,"PeriodicalName":"Polymer Science, Series D","FirstCategoryId":"1","ListUrlMain":"https://link.springer.com/article/10.1134/S1995421224701387","RegionNum":0,"RegionCategory":null,"ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"Q4","JCRName":"Materials Science","Score":null,"Total":0}
引用次数: 0
Abstract
Some aspects of the problem of adhesive fracture of aircraft panels made of composite materials under fatigue loading are considered. Algorithms of computer modeling of the delamination development process are described. Various methods of nondestructive testing for identifying the size and location of adhesive failure are analyzed. The cause of adhesion failure between anisotropic layers even under uniaxial tension is explained. The growth of delamination area under cyclic tension is described by an equation in the form of a power-law dependence on the range of the elastic energy release rate. For aircraft panels made of laminated carbon-fiber-reinforced plastics, the independence of the delamination growth rate from its current area is experimentally confirmed.
期刊介绍：
Polymer Science, Series D publishes useful description of engineering developments that are related to the preparation and application of glues, compounds, sealing materials, and binding agents, articles on the adhesion theory, prediction of the strength of adhesive joints, methods for the control of their properties, synthesis, and methods of structural modeling of glued joints and constructions, original articles with new scientific results, analytical reviews of the modern state in the field.
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