Hostname: page-component-76fb5796d-zzh7m Total loading time: 0 Render date: 2024-04-26T09:27:17.308Z Has data issue: false hasContentIssue false
  • English
  • Français

Design, analysis and experimental validation of a morphing UAV wing

Part of: Smart Aircraft

Published online by Cambridge University Press:  27 January 2016

M. Bolinches ,
A. J. Keane ,
A. I. J. Forrester ,
J. P. Scanlan  and
K. Takeda
M. Bolinches
Affiliation:
University of Southampton, Southampton, UK
A. J. Keane*
Affiliation:
University of Southampton, Southampton, UK
A. I. J. Forrester
Affiliation:
University of Southampton, Southampton, UK
J. P. Scanlan
Affiliation:
University of Southampton, Southampton, UK
K. Takeda
Affiliation:
University of Southampton, Southampton, UK
*
andy.keane@soton.ac.uk
Get access Rights & Permissions [Opens in a new window]

Abstract

The design of wings with morphing capabilities is known to give aerodynamic benefits. These aero-dynamic benefits come from both the use of hinge-less surfaces and the greater adaptability to flight conditions. This paper describes the structural design of a twisting wing to be used for an unmanned air vehicle (UAV) and presents finite element analysis and experiment results. This is part of a research project carried out at the University of Southampton in which one of the goals is to compare different novel wing designs and technologies to determine which one of them gives the best performance. The twisting capability provides roll control without hinged surfaces hence providing aerodynamic improvement. The wing is manufactured using polystyrene foam and is cut out of block of this material using a hot wire machine. In order to link this foam structure to a main spar, ABS plastic inserts were manufactured using a 3D printer. The mechanisms used to actuate the wing are also made from this material. A full scale UAV wing has been manufactured and tested in order to compare with FEA results.

Type
Research Article
Information
The Aeronautical Journal , Volume 115 , Issue 1174 , December 2011 , pp. 761 - 765
Copyright
Copyright © Royal Aeronautical Society 2011 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Gamboa, P., Alexio, P., Vale, J., Lau, F. and Suleman, A. Design and testing of a morphing wing for an experimental UAV, NATO RTO.Google Scholar
2. Lt Cdr Ware, M. UAVs in an Australian maritime, Seahawk Observer, Royal Australian Navy, Australia.Google Scholar
3. Hibbbert, L. The sky’s the limit Professional Engineering, 2 June 2010.Google Scholar
4. Friswell, M.I. and Inman, D.J. Morphing Concepts for UAVs 21st Bristol UAV Systems Conference.Google Scholar
5. Friswell, M.I., Baker, D., Herencia, J.E., Mattioni, F. and Weaver, P.M. Compliant Structures for Morphing Aircraft Proceedings of ICAST2006: 17th International Conference on Adaptive Structures and Technologies.Google Scholar
6. Saggere, L. and Kota, S. Static shape control of smart structures using compliant mechanisms, AIAA J.Google Scholar
7. Portela, P., Camanho, P. and Weaver, P. and Bond, I. Analysis of morphing, multi stable structures actuated by piezoelectric patches, Computers and Structures.Google Scholar
8. Hufenbach, W., Gude, M. and Kroll, L. Design of multistable composites for application in adaptive structures, Composites science and technology.Google Scholar
9. Vos, R., Grdal, Z. and Abdalla, M. Mechanism for warp-controlled twist of a morphing wing, J Aircr, 2010.Google Scholar
10. Ursache, N.M., Keane, A.J. and Bresslof, N.W. On the Design of Morphing Airfoils using Spinal Structures 47th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference 2006.Google Scholar
11. Ursache, N.M. The Design of Adaptive Structures for Wing Morphing, PHD thesis, 2006.Google Scholar
12. Phillips, W.F., Fugal, S.R. and Spall, R.E. minimizing induced drag with wing twist, computational-fluid-dynamics validation, J Aircr.Google Scholar
13. Phillips, W.F. Lifting-line analysis for twisted wings and washout optimized wings, J Aircr.Google Scholar