Performance measurements of a dual-rotor arm mechanism for efficient flight transition of fixed-wing unmanned aerial vehicles

dc.contributor.advisorMaldonado, Victor
dc.contributor.authorMcGill, Karen Ashley Jean
dc.contributor.committeeMemberWan, Hung-Da
dc.contributor.committeeMemberDong, Bing
dc.date.accessioned2024-02-12T15:40:18Z
dc.date.available2024-02-12T15:40:18Z
dc.date.issued2014
dc.descriptionThis item is available only to currently enrolled UTSA students, faculty or staff. To download, navigate to Log In in the top right-hand corner of this screen, then select Log in with my UTSA ID.
dc.description.abstractReconfigurable systems are a class of systems that can be transformed into different configurations, generally to perform unique functions or to maintain operational efficiency under distinct conditions. A UAV can be considered a reconfigurable system when coupled with various useful features such as vertical take-off and landing (VTOL), hover capability, long-range, and relatively large payload. Currently, a UAV having these capabilities is being designed by the UTSA Mechanical Engineering department. UAVs such as this one have the following potential uses: emergency response/disaster relief, hazard-critical missions, offshore oil rig/wind farm delivery, surveillance, etc. The goal of this thesis is to perform experimental thrust and power measurements for the propulsion system of this fixed-wing UAV. Focus was placed on a rotating truss arm supporting two brushless motors and rotors that will later be integrated to the ends of the UAV wing. These truss arms will rotate via a supporting shaft from 0° to 90° to transition the UAV between a vertical take-off, hover, and forward flight. To make this hover/transition possible, a relationship between thrust, arm angle, and power drawn was established by testing the performance of the arm/motor assembly at arm angles of 0°, 15°, 30°, 45°, 60°, 75°, and 90°. Universal equations for this system of thrust as a function of the arm angle were created by correlating data collected by a load cell. A Solidworks model was created and used to conduct fluid dynamics simulations of the streamlines over the arm/motor assembly.
dc.description.departmentMechanical Engineering
dc.format.extent53 pages
dc.format.mimetypeapplication/pdf
dc.identifier.isbn9781321194821
dc.identifier.urihttps://hdl.handle.net/20.500.12588/4639
dc.languageen
dc.subjectDrone
dc.subjectHover
dc.subjectUAS
dc.subjectUnmanned aerial systems
dc.subjectUAV
dc.subjectUnmanned aerial vehicle
dc.subjectVTOL
dc.subjectVertical take-off and landing
dc.subject.classificationMechanical engineering
dc.subject.classificationAerospace engineering
dc.titlePerformance measurements of a dual-rotor arm mechanism for efficient flight transition of fixed-wing unmanned aerial vehicles
dc.typeThesis
dc.type.dcmiText
dcterms.accessRightspq_closed
thesis.degree.departmentMechanical Engineering
thesis.degree.grantorUniversity of Texas at San Antonio
thesis.degree.levelMasters
thesis.degree.nameMaster of Science

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