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Dynamic analysis of modified composite helicopter blade

dc.creatorGarinis, Dimitrios
dc.creatorDinulović, Mirko
dc.creatorRašuo, Boško
dc.date.accessioned2022-09-19T17:03:09Z
dc.date.available2022-09-19T17:03:09Z
dc.date.issued2012
dc.identifier.issn1451-2092
dc.identifier.urihttps://machinery.mas.bg.ac.rs/handle/123456789/1580
dc.description.abstractU ovom radu izvršena je modalna analiza modifikovane lopatice helikoptera 'Gazela'. Modifikovana lopatica je kompletno kompozitna sa saćastom ispunom. Prikazan je metod određivanja modova oscilovanja i sopstvenih frekvencija. Modifikovana lopatica sastoji se od saćaste ispune, ramenjače od 3D usmerenog kompozita i tankih karbonskih ploča kao oplate. Da bi se odredila matrica krutosti ispune korišćen je metod ekvivalentnih masa. U cilju nalaženja optimalnog metoda za određivanje sopstvenih frekvencija ispitano je nekoliko poznatih metoda. Metod Lancosa pokazao je najtačnije rezultate kroz umereno procesorsko vreme kada je u pitanju određivanje sopstvenih frekvencija i modova oscilovanja kod struktura od kompozitnih materijala sa saćastim ispunama. Ovom metodom izračunata su prva četiri moda oscilovanja modifikovane kompozitne lopatice, i prikazani su rezultati modova oscilovanja i deformacione energije lopatice.sr
dc.description.abstractIn the present study, modal analysis has been performed on modified Gazelle helicopter blade. The construction of the blade is fully composite with the honeycomb core. The approach to determining structure mode shapes and natural frequencies is presented. Modified blade consists of core material, 3D unidirectional composite spar and thin carbon composite facesheets as blade skin. To determine the stiffness of the honeycomb core, the equivalent mass approach was used. Several methods of eigenvalue extraction have been investigated in order to find optimal method which can be used in dynamic analysis of composite structures containing honeycomb cores. Among all extraction methods investigated, it was found that combined Lanczos method is most effective in terms of accuracy and CPU time for eigenvalue extraction in composite structures with honeycomb core having large number of degrees of freedom. Strain energies for first four mode shapes of modified helicopter blade have been calculated using numerical approach and results are presented.en
dc.publisherUniverzitet u Beogradu - Mašinski fakultet, Beograd
dc.rightsopenAccess
dc.rights.urihttps://creativecommons.org/licenses/by/4.0/
dc.sourceFME Transactions
dc.subjectnormal modeen
dc.subjectnatural frequenciesen
dc.subjecthexagonal honeycomb coreen
dc.subjecthelicopter composite bladeen
dc.subjectcarbon fiberen
dc.titleDinamička analiza modifikovane helikopterske lopatice od kompozitnih materijalasr
dc.titleDynamic analysis of modified composite helicopter bladeen
dc.typearticle
dc.rights.licenseBY
dc.citation.epage68
dc.citation.issue2
dc.citation.other40(2): 63-68
dc.citation.rankM24
dc.citation.spage63
dc.citation.volume40
dc.identifier.fulltexthttp://machinery.mas.bg.ac.rs/bitstream/id/446/1577.pdf
dc.identifier.rcubhttps://hdl.handle.net/21.15107/rcub_machinery_1580
dc.identifier.scopus2-s2.0-84865541745
dc.type.versionpublishedVersion


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