Full metadata record
| DC Field | Value | Language |
|---|---|---|
| dc.contributor | Department of Mechanical Engineering | en_US |
| dc.contributor.advisor | Wen, Chih-yung (AAE) | en_US |
| dc.creator | Zhou, Qianyu | - |
| dc.identifier.uri | https://theses.lib.polyu.edu.hk/handle/200/11471 | - |
| dc.language | English | en_US |
| dc.publisher | Hong Kong Polytechnic University | en_US |
| dc.rights | All rights reserved | en_US |
| dc.title | Conceptual design and analysis of a tail-sitter unmanned aerial vehicle (UAV) | en_US |
| dcterms.abstract | The tail-sitter vertical take-off and landing UAV has the characteristics of both multi-rotor and fixed-wing. It can both take off and land vertically and fly horizontally with fixed-wing. Due to its unique take-off and landing and cruise performance, the tail-sitter vertical take-off and landing UAV is widely used in power detection, express transportation, aerial surveying, and other scenarios. Due to its broad application prospects, it is of great significance to research this type of UAV. However, due to the lack of detailed system data support, the structural design of the tail-sitter vertical take-off and landing UAV is more difficult. At the same time, when the drone carries a certain weight of the payload, its flight performance will be more tested. In response to the above-mentioned problems, based on the structure of the flying wing aircraft, this thesis has designed a tail-sitter dual-rotor flying wing vertical take-off and landing UAV solution and carries out a detailed and systematic design. First of all, according to the design requirements of the tail-sitter dual-rotor flying wing vertical take-off and landing UAV, the overall design and main parameters of the UAV were determined. And use the CFD method to analyze the aerodynamic characteristics of the designed aircraft. The stall performance of an airplane with a small aspect ratio is good. The maximum lift-to-drag ratio is 11. The aircraft's stall angle of attack is 23°. Then according to the structural design requirements and criteria, the detailed structural design of the flying wing layout is carried out. It mainly includes wing, lift ailerons, fuselage, motor bracket, and landing gear, and other components. Theoretically, these works were achieved, and this report will demonstrate the details of the works done stated above. | en_US |
| dcterms.extent | xii, 113 pages : color illustrations | en_US |
| dcterms.isPartOf | PolyU Electronic Theses | en_US |
| dcterms.issued | 2021 | en_US |
| dcterms.educationalLevel | M.Sc. | en_US |
| dcterms.educationalLevel | All Master | en_US |
| dcterms.LCSH | Drone aircraft -- Design and construction | en_US |
| dcterms.LCSH | Hong Kong Polytechnic University -- Dissertations | en_US |
| dcterms.accessRights | restricted access | en_US |
Files in This Item:
| File | Description | Size | Format | |
|---|---|---|---|---|
| 5945.pdf | For All Users (off-campus access for PolyU Staff & Students only) | 5.65 MB | Adobe PDF | View/Open |
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