Design, Fabrication, and Experimental Analysis of Tiltrotor Mechanism

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dc.contributor.advisorKarki, Ashish
dc.contributor.authorLuitel, Kshitij
dc.contributor.authorKoirala, Kushal Sharma
dc.contributor.authorGurung, Monika
dc.contributor.authorDahal, Ujjwal
dc.date.accessioned2024-08-13T06:11:22Z
dc.date.available2024-08-13T06:11:22Z
dc.date.issued2024-03
dc.descriptionThis paper presents the design and synthesis of a tilt-rotor mechanism for a hybrid UAV that can perform vertical takeoff and landing (VTOL) and fixed-wing flight. The tilt-rotor mechanism allows the orientation of the propulsion system to change from vertical to horizontal or vice versa, enabling the UAV to fly like a helicopter or an airplane.
dc.description.abstractThis paper presents the design and synthesis of a tilt-rotor mechanism for a hybrid UAV that can perform vertical takeoff and landing (VTOL) and fixed-wing flight. The tilt-rotor mechanism allows the orientation of the propulsion system to change from vertical to horizontal or vice versa, enabling the UAV to fly like a helicopter or an airplane. The paper describes the design, mathematical modeling, structural analysis, and fabrication of the mechanism, as well as the design and testing of a test bench and a control system. The paper also evaluates the performance of the mechanism and the system on a bi-copter UAV model and discusses the challenges, limitations, and future enhancements of the project. The paper concludes that the tilt-rotor mechanism is a promising solution for hybrid UAVs that can combine the advantages of both rotorcraft and fixed-wing UAVs.
dc.identifier.urihttps://hdl.handle.net/20.500.14540/22675
dc.language.isoen
dc.publisherI.O.E
dc.subjectTilt-rotor mechanism
dc.subjectBi-copter
dc.subjectFixed wing
dc.titleDesign, Fabrication, and Experimental Analysis of Tiltrotor Mechanism
dc.typeTechnical Report
local.academic.levelOther
local.institute.titleInstitute of Engineering
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