Improvement of UAV: design and implementation on launchability

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dc.authoridErsoy, Sezgin/0000-0002-4029-5603
dc.authorwosidErsoy, Sezgin/A-7594-2019
dc.contributor.authorGokbel, Etka
dc.contributor.authorGullu, Aydin
dc.contributor.authorErsoy, Sezgin
dc.date.accessioned2024-06-12T11:16:57Z
dc.date.available2024-06-12T11:16:57Z
dc.date.issued2023
dc.departmentTrakya Üniversitesien_US
dc.description.abstractPurposeThis study aims to a launchable design has been made to prevent wasted time in time-critical areas, and increase the efficiency of the unmanned aerial vehicle (UAV). In this way, a UAV can reach the mission height quickly. Design/methodology/approachA unique launchable UAV and launcher mechanism have been designed. The launchable UAV will be folded into the launcher mechanism and will automatically start flight after launch. The study includes mathematical calculations, 3D designs steps and produced UAV tests for the designed UAV. The launcher mechanism was designed in accordance with the tests for the UAV, and appropriate choices were made for the altitude and launch acceleration required by the UAV. According to the calculations, material selection and production were made. FindingsIn the tests, the climbing time was reduced by 1 s compared with the existing UAVs. With the launch, it enabled it to reach the altitude quickly and silently. In addition, because the launch energy was provided externally, it provided an advantage for the flight time. Practical implicationsA rotary-wing UAV with a launch mechanism and a fast launch was designed and prototyped. The maximum climb speed of the designed drone is 6.52 m/s. Frame arm length is 9.2 cm, propeller diameter is 15.24 cm and hover flight time is 7.2 m. Originality/valueThe UAV design can be launched. Design, calculation and experimental studies have been carried out for rapid take-off of the rotary wing UAV. The parts used in the UAV are originally produced. It is not a commercial product.en_US
dc.identifier.doi10.1108/AEAT-06-2022-0153
dc.identifier.endpage740en_US
dc.identifier.issn1748-8842
dc.identifier.issn1758-4213
dc.identifier.issue5en_US
dc.identifier.scopus2-s2.0-85143791847en_US
dc.identifier.scopusqualityN/Aen_US
dc.identifier.startpage734en_US
dc.identifier.urihttps://doi.org/10.1108/AEAT-06-2022-0153
dc.identifier.urihttps://hdl.handle.net/20.500.14551/24499
dc.identifier.volume95en_US
dc.identifier.wosWOS:000897611900001en_US
dc.identifier.wosqualityQ3en_US
dc.indekslendigikaynakWeb of Scienceen_US
dc.indekslendigikaynakScopusen_US
dc.language.isoenen_US
dc.publisherEmerald Group Publishing Ltden_US
dc.relation.ispartofAircraft Engineering And Aerospace Technologyen_US
dc.relation.publicationcategoryMakale - Uluslararası Hakemli Dergi - Kurum Öğretim Elemanıen_US
dc.rightsinfo:eu-repo/semantics/closedAccessen_US
dc.subjectUnmanned Aerial Vehicleen_US
dc.subjectVertical Take-Off And Landingen_US
dc.subjectLaunched UAVen_US
dc.subjectLaunch Mechanismen_US
dc.subjectFlight Accuracyen_US
dc.titleImprovement of UAV: design and implementation on launchabilityen_US
dc.typeArticleen_US

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