Design of a Small UAV Combined Between Flying-Wing and Quadrotor with XFRL5
International Journal of Transportation Engineering and Technology
Volume 2, Issue 4-1, December 2016, Pages: 1-6
Received: Apr. 13, 2016; Accepted: Jul. 22, 2016; Published: Sep. 3, 2016
Views 5196      Downloads 147
Authors
Ngo Khanh Hieu, Department of Aerospace Engineering, Ho Chi Minh City University of Technology, Ho Chi Minh City, Vietnam
Pham Quang Vinh, Department of Aerospace Engineering, Ho Chi Minh City University of Technology, Ho Chi Minh City, Vietnam
Dinh Anh Bao, Department of Aerospace Engineering, Ho Chi Minh City University of Technology, Ho Chi Minh City, Vietnam
Article Tools
Follow on us
Abstract
The design process of a product is a multi-step process of selection and assessment criteria to create a final product which meets all the needs of the practice. A small UAV combined between flying-wing and quadrotor is a very complex product, so the design process of this small UAV requires a thorough and circumspect review. The problem is how to optimize the design and to carry out the testing of the feasibility of design requirements with the lowest cost and time savings. For that reason, many tools of Multi-Fidelity Analysis for UAV such as XFLR5, XFoil… have been used to give considerable support for this design process. This research focusses mainly on the analysis/design of the configuration of a small UAV flying wing based on the performance at its cruise speed.
Keywords
Small UAV Flying-wing, Quadrotor, XFRL5, Airfoil Selection for Small UAV
To cite this article
Ngo Khanh Hieu, Pham Quang Vinh, Dinh Anh Bao, Design of a Small UAV Combined Between Flying-Wing and Quadrotor with XFRL5, International Journal of Transportation Engineering and Technology. Special Issue:Experiments Researches in Aeronautical Engineering. Vol. 2, No. 4-1, 2016, pp. 1-6. doi: 10.11648/j.ijtet.s.2016020501.11
Copyright
Copyright © 2016 Authors retain the copyright of this article.
This article is an open access article distributed under the Creative Commons Attribution License (http://creativecommons.org/licenses/by/4.0/) which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
References
[1]
S. Verling, J. Zilly, Modeling and Control of a VTOL Glider, Bachelor thesis, ETH, Zurich, 2013.
[2]
M. Hochstenbach, C. Notteboom, Design and control of an unmanned aerial vehicle for autonomous parcel delivery with transition for vertical take-off to forward flight, Bachelor thesis, KU Leuven, Belgium, 2014.
[3]
http://www.xflr5.com/xflr5.htm, XFLR5 V 6.09.
[4]
M. Drela, “XFOIL: An analysis and design system for low Reynolds number airfoils”. In T. J. Mueller, editor, Low Reynolds Number Aerodynamics. Springer-Verlag, Jun 1989. http://web.mit.edu/drela/Public/web/xfoil
[5]
Anh Bao DINH, Khanh Hieu NGO, Nhu Van Nguyen, An Efficient Low-Speed Airfoil Design Optimization Process Using Multi-Fidelity Analysis for UAV Flying Wing, Journal of Science & Technology Development, Vietnam National University, Ho Chi Minh City (accepted 05/2016).
[6]
Ngo Khanh Hieu, Huynh Thien Loc, Airfoil Selection for Fixed Wing of Small Unmanned Aerial Vehicles, AETA2015: Recent Advanced in Electrical Engineering and Related Sciences, Ho Chi Minh City, Vietnam, 2015.
[7]
Michael S. Selig, Christopher A. Lyon, Philippe Giguère, Cameron P. Ninham, and James J. Guglielmo, Summary of Low Speed airfoil data Volume 2, Department of Aerospace Engineering, University of Illinois at Urbana-Champaign, 1996.
[8]
Christopher A. Lyon, Andy P. Broeren, Philippe Giguère, Ashok Gopalarathnam, and Michael S. Selig, Summary of Low Speed airfoil data Volume 3, Department ofAerospace Engineering, University of Illinois at Urbana-Champaign, 1997.
[9]
Gregory A Williamson, Bryan D. McGranahan, Benjamin A. Broughton, Robert W. Deters, John B. Brandt and M. S. Selig, Summary of Low Speed airfoil data Volume 5, Department ofAerospace Engineering, University of Illinois at Urbana-Champaign, 2012.
[10]
Ngo Khanh Hieu, Bui Khac Huy, Electric RC Model Airplane carrying payload up to 300 grams: Design and Manufacture, the 4th AUN/SEED-Net Regional Conference in Mechanical and Aerospace Technology, Ho Chi Minh City, Vietnam, 2012.
[11]
Robert C. Nelson, Flight Stability and Automatic Control, McGraw-Hill Education, 2nd edition, 1997.
[12]
Roskam, Method for Estimating Drag Polars of Subsonic Airplanes, Aviation and Engineering corporation, 1983.
ADDRESS
Science Publishing Group
548 FASHION AVENUE
NEW YORK, NY 10018
U.S.A.
Tel: (001)347-688-8931