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Modeling and Experimental Evaluation of a Tilt Wing UAV
2015 (English)Independent thesis Advanced level (professional degree), 20 credits / 30 HE creditsStudent thesis
Abstract [en]

The aim of this thesis is to design an optimal model for describing the behavior of a tilt wing UAV during its transitional state from a helicopter to an airplane and to perform an experimental evaluation of its validity. A tilt wing UAV can be described as a hybrid between a helicopter and a plane, which has the capabilities of both aircrafts, meaning it can stand still and hover, and by tilting its wing 90 degrees, act like a regular plane. This would imply that the aircraft can have vertical take offs and landings, stand still and hover in mid air, while being able to travel long distances efficiently. The novelty of this thesis stems from: a) the simulations on the main wing during the transition between helicopter and fixed-wing plane mode for angles between 0-90 degrees, b) comparison between the model extracted from the simulations for the main wing and tests from a wind tunnel and, c) reaching a sufficiently good design for a tilt wing UAV with, d) an overall experimental evaluation.

Place, publisher, year, edition, pages
2015. , 80 p.
Keyword [en]
Keyword [sv]
Teknik, UAV, Tilt wing, Tilt-wing, ANSYS, wind tunnel
URN: urn:nbn:se:ltu:diva-49602Local ID: 6ecd9674-99f5-4d0c-93b0-a69fe189f6a3OAI: diva2:1022949
Subject / course
Student thesis, at least 30 credits
Educational program
Space Engineering, master's level
Validerat; 20141223 (global_studentproject_submitter)Available from: 2016-10-04 Created: 2016-10-04Bibliographically approved

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