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Procena preostalog veka elemenata avionskih konstrukcija sa inicijalnim prskotinama
Residual life estimation of cracked aircraft structural components
dc.creator | Maksimović, Mirko S. | |
dc.creator | Vasović, Ivana | |
dc.creator | Maksimović, Katarina | |
dc.creator | Trišović, Nataša | |
dc.creator | Maksimović, Stevan M. | |
dc.date.accessioned | 2022-09-19T18:25:35Z | |
dc.date.available | 2022-09-19T18:25:35Z | |
dc.date.issued | 2018 | |
dc.identifier.issn | 1451-2092 | |
dc.identifier.uri | https://machinery.mas.bg.ac.rs/handle/123456789/2793 | |
dc.description.abstract | Predmet ovog istraživanja je usmeren na uspostavljanje proračunske procedure za analizu čvrstoće elemenata avionskih konstrukcija sa aspekta zamora i mehanike loma. Za tu svrhu ovde će biti uspostavljena proračunska procedura za procenu preostalog veka elemenata avionskih konstrukcija tipa dela oplate krila i uški pod dejstvom cikličnih opterećenja konstantne amplitude i spektra opterećenja. Poseban aspekt istraživanja se odnosi na primenu gustine energije deformacije (GED) za procenu preostalog veka elemenata konstrukcija sa inicijalnim oštećenjima tipa prskotina. Za određivanje analitičkih izraza za faktore intenziteta napona ovde su korišćeni specijalni singularni konačni elementi. Verifikacija proračunskih procedura za procene preostalog veka je podržana sa sa analitičkim i eksperimentalnim rezultatima uključivši i testove na zamor posebno sa aspekta eksperimentalnog određivanja malociklusnih zamornih karakteristika materijala. | sr |
dc.description.abstract | The subject of this investigation is focused on developing computation procedure for strength analysis of damaged aircraft structural components with respect to fatigue and fracture mechanics. For that purpose, here will be defined computation procedures for residual life estimation of aircraft structural components such as wing skin and attachment lugs under cyclic loads of constant amplitude and load spectrum. A special aspect of this investigation is based on using of the Strain Energy Density (SED) method in residual life estimation of structural elements with initial cracks. To determine analytic formulae for the stress intensity factors here singular finite elements are used. Verification of computation procedures for residual life estimations will be supported with corresponding experimental tests for determination of low cyclic fatigue properties of materials and corresponding parameters of fracture mechanics, including fatigue tests of representative aircraft structural elements. | en |
dc.publisher | Univerzitet u Beogradu - Mašinski fakultet, Beograd | |
dc.relation | info:eu-repo/grantAgreement/MESTD/Technological Development (TD or TR)/35011/RS// | |
dc.relation | info:eu-repo/grantAgreement/MESTD/Basic Research (BR or ON)/174001/RS// | |
dc.rights | openAccess | |
dc.rights.uri | https://creativecommons.org/licenses/by/4.0/ | |
dc.source | FME Transactions | |
dc.subject | fracture mechanics | en |
dc.subject | finite element method | en |
dc.subject | damage tolerance approach | en |
dc.subject | crack growth | en |
dc.subject | aircraft constructions | en |
dc.title | Procena preostalog veka elemenata avionskih konstrukcija sa inicijalnim prskotinama | sr |
dc.title | Residual life estimation of cracked aircraft structural components | en |
dc.type | article | |
dc.rights.license | BY | |
dc.citation.epage | 128 | |
dc.citation.issue | 1 | |
dc.citation.other | 46(1): 124-128 | |
dc.citation.rank | M24 | |
dc.citation.spage | 124 | |
dc.citation.volume | 46 | |
dc.identifier.doi | 10.5937/fmet1801124M | |
dc.identifier.fulltext | http://machinery.mas.bg.ac.rs/bitstream/id/1490/2790.pdf | |
dc.identifier.scopus | 2-s2.0-85042689800 | |
dc.identifier.wos | 000417363400017 | |
dc.type.version | publishedVersion |