Design and performance analyses of a fixed wing battery VTOL UAV

Basit Öğe Kaydı
dc.contributor.authorDundar, Ozgur
dc.contributor.authorBilici, Mesut
dc.contributor.authorUnler, Tarik
dc.date.accessioned2024-02-23T14:12:48Z
dc.date.available2024-02-23T14:12:48Z
dc.date.issued2020
dc.departmentNEÜen_US
dc.description.abstractThe objective of this paper is to explain the design steps and performance analyses including energy consumption of a fixed-wing (FW) vertical take-off and landing (VTOL) unmanned air vehicle (UAV). The vehicle is designed from the beginning with the goal for low take-off weight and high aerodynamic performance. Aerodynamic design steps and sizing of both wing and control surfaces are demonstrated and static stability is fulfilled by evaluating the center of gravity location with respect to neutral point. In addition, power requirements and energy consumptions for take-off, climbing, cruise and landing are evaluated in perspective of flight performances to find out the required endurance for each flight condition. In order to do that selected battery is modelled in Simulink and results are represented. In take-off and landing flight conditions, momentum theory is implemented for vertical flight while the cruise flight is utilized to find out the maximum endurance. Drag calculations in level flight are performed in detail to experience the drawbacks of multi-rotor system including propellers providing vertical flight. Finally, VTOL-FW concept having multi-rotor system with four extra propellers and only fixed wing (FW) concept are compared in terms of endurance. It is found that FW concept without multi-rotor system with four propellers have much more endurance compared to VTOL-FW concept. Manufacturing with three-dimensional printers and flight tests of VTOL-FW UAV will be performed as a future work. (c) 2020 Karabuk University. Publishing services by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/).en_US
dc.identifier.doi10.1016/j.jestch.2020.02.002
dc.identifier.endpage1193en_US
dc.identifier.issn2215-0986
dc.identifier.issue5en_US
dc.identifier.scopus2-s2.0-85080036949en_US
dc.identifier.scopusqualityQ1en_US
dc.identifier.startpage1182en_US
dc.identifier.urihttps://doi.org/10.1016/j.jestch.2020.02.002
dc.identifier.urihttps://hdl.handle.net/20.500.12452/12189
dc.identifier.volume23en_US
dc.identifier.wosWOS:000576840300009en_US
dc.identifier.wosqualityQ1en_US
dc.indekslendigikaynakWeb of Scienceen_US
dc.indekslendigikaynakScopusen_US
dc.language.isoenen_US
dc.publisherElsevier - Division Reed Elsevier India Pvt Ltden_US
dc.relation.ispartofEngineering Science And Technology-An International Journal-Jestechen_US
dc.relation.publicationcategoryMakale - Uluslararası Hakemli Dergi - Kurum Öğretim Elemanıen_US
dc.rightsinfo:eu-repo/semantics/openAccessen_US
dc.subjectVtolen_US
dc.subjectBattery Powered Uaven_US
dc.subjectAerodynamic Designen_US
dc.subjectPerformance Calculationsen_US
dc.subjectMaximum Enduranceen_US
dc.titleDesign and performance analyses of a fixed wing battery VTOL UAVen_US
dc.typeArticleen_US

Dosyalar

Koleksiyon

WoS İndeksli Yayınlar Koleksiyonu
Scopus İndeksli Yayınlar Koleksiyonu