Hostname: page-component-586b7cd67f-2plfb Total loading time: 0 Render date: 2024-11-25T10:44:28.033Z Has data issue: false hasContentIssue false
  • English
  • Français

Multi-parametric flutter analysis of a morphing wing trailing edge

Part of: Smart Aircraft

Published online by Cambridge University Press:  27 January 2016

R. Pecora ,
M. Magnifico ,
F. Amoroso  and
E. Monaco
R. Pecora*
Affiliation:
University of Naples, ‘Federico II’x, Department of Aerospace Engineering, Napoli, Italy
M. Magnifico
Affiliation:
University of Naples, ‘Federico II’x, Department of Aerospace Engineering, Napoli, Italy
F. Amoroso
Affiliation:
University of Naples, ‘Federico II’x, Department of Aerospace Engineering, Napoli, Italy
E. Monaco
Affiliation:
University of Naples, ‘Federico II’x, Department of Aerospace Engineering, Napoli, Italy
*
[email protected]
Get access Rights & Permissions [Opens in a new window]

Abstract

The development of adaptive morphing wings has been individuated as one of the crucial topics in the greening of the next generation air transport. Research programs are currently running worldwide to exploit the potentiality of morphing concepts in the optimisation of aircraft efficiency and in the consequent reduction of fuel burn. Among these, SARISTU represents the largest European funded research project which ambitiously addresses the challenges posed by the physical integration of smart concepts in real aircraft structures; for the first time ever, SARISTU will experimentally demonstrate the structural feasibility of individual morphing concepts concerning the leading edge, the trailing edge and the winglet on a full-size outer wing belonging to a CS-25 category aircraft. In such framework, the authors intensively worked on the definition of aeroelastically stable configurations for a morphing wing trailing edge driven by conventional electromechanical actuators. Trade off aeroelastic analyses were performed in compliance with CS-25 airworthiness requirements (paragraph 25.629, parts (a) and (b)-(1)) in order to define safety ranges for trailing-edge inertial and stiffness distributions as well as for its control harmonics. Rational approaches were implemented in order to simulate the effects induced by variations of trailing-edge actuators’ stiffness on the aeroelastic behaviour of the wing also in correspondence of different dynamic properties of the trailing-edge component. Reliable aeroelastic models and advanced computational strategies were properly implemented to enable fast flutter analyses covering several configuration cases in terms of structural system parameters. Already available finite elements models were processed in MSC-NASTRAN® environment to evaluate stiffness and inertial distributions suitable for the stick-equivalent idealisation of the reference structure. A parametric stick-equivalent model of the reference structure was then generated in SANDY3.0, an in-house developed code, that was used for the definition of the coupled aero-structural model as well as for the solution of aeroelastic stability equations by means of theoretical modes association in frequency domain.

Obtained results were finally arranged in stability carpet plots efficiently conceived to provide guidelines for the preliminary design of the morphing trailing-edge structure and therein embedded actuators.

Type
Research Article
Information
The Aeronautical Journal , Volume 118 , Issue 1207 , September 2014 , pp. 1063 - 1078
Copyright
Copyright © Royal Aeronautical Society 2014 

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. Barbarino, S., Bilgen, O., Ajaj, R.M., Friswell, M.I. and Inman, D.J. A review of morphing aircraft, J Intelligent Material Systems and Structures, 2011, 22, pp 823–877.Google Scholar
2. Monner, H.P., Bein, T., Hanselka, H. and Breitbach, E. Design Aspects of the Adaptive Wing – The Elastic Trailing Edge and the Local Spoiler Bump, Proceedings of Royal Aeronautical Society Symposium on Multidisciplinary Design and Optimization, Royal Aeronautical Society Publishing, London, UK, 1998, pp 15.1–15.9.Google Scholar
3. Pecora, R., Barbarino, S., Concilio, A., Lecce, L. and Russo, S. Design and functional test of a morphing high-lift device for a regional aircraft, J Intelligent Material Systems and Structures, 2011, 22, (10), pp 1005–1023.Google Scholar
4. Pecora, R., Amoroso, F. and Lecce, L. Effectiveness of wing twist morphing in roll control, J Aircr, 2012, 49, issue 6, pp 1666–1674.Google Scholar
5. Barbarino, S., Pecora, R., Lecce, L., Concilio, A., Ameduri, S. and De Rosa, L. Airfoil structural morphing based on s.m.a. actuator series: numerical and experimental results, J Intelligent Material Systems and Structures, 2011, 22, pp 987–1004.Google Scholar
6. Stanewsky, E. Adaptive wing and flow control technology, Progress in Aerospace Sciences, 2001, 37, (7), pp 583–667.Google Scholar
7. Browman, J., Sanders, B. and Weisshaar, T. Evaluating the Impact of Morphing Technologies on Aircraft Performance, Proceedings of the Forty-Third AIAA Conference on Structures, Structural Dynamics and Materials, AIAA Paper 2002-1631, April 2002.Google Scholar
8. Szodruch, J. and Hilbig, R. Variable wing camber for transport aircraft, Progress in Aerospace Science, 1988, 25, (3), pp 297–328.Google Scholar
9. Munday, D. and Jacob, J. Active Control of Separation on a Wing with Conformal Camber, Proceedings of the Thirty-Ninth AIAA Aerospace Science Meeting and Exhibit, AIAA Paper 2001-293, January 2001.Google Scholar
10. Perkins, D.A., Reed, J.L. and Havens, E. Morphing Wing Structures for Loitering Air Vehicles, Proceedings of the Forty-Fifth AIAA Confrence on Structures, Structural Dynamics and Materials, AIAA Paper 2004-1888, April 2004.Google Scholar
11. Blondeau, J. and Pines, D. Pneumatic Morphing Aspect Ratio Wing, Proceedings of the Forty-Fifth AIAA Conference on Structures, Structural Dynamics and Materials, AIAA Paper 2004-1808, April 2004.Google Scholar
12. Courchesne, S., Popov, A.-V. and Botez, R.M. New aeroelastic studies for a morphing wing, INCAS Bulletin, 2012, 4, (2), pp 19–28.Google Scholar
(13) Botez, R.M., Molaret, P. and Laurendeau, E. Laminar Flow Control on a Research Wing Project Presentation Covering a Three Year Period, Canadian Aeronautics and Space Institute (CASI) Aircraft Design and Development Symposium, Toronto, Canada, April 2007.Google Scholar
14. www.saristu.eu (web site of the SARISTU project)Google Scholar
15. Dimino, I., Concilio, A., Schueller, M. and Gratias, A. An adaptive control system for wing TE shape control, Proceedings of SPIE 8690, Industrial and Commercial Applications of Smart Structures Technologies, March 2013 (DOI: 10.1117/12.2012187).Google Scholar
16. Dimino, I., Schueller, M., Gratias, A. and Flauto, D. Adaptive Shape Control Architecture for Morphing Wings, Proceedings of the 6th ECCOMAS thematic Conference on Smart Structures and Materials (SMART 2013), June 2013.Google Scholar
17. European Aviation Safety Agency, Certifcation Specifcations and Acceptable Means of Compliance for Large Aeroplanes – CS-25, Amendment 11 July 2011.Google Scholar
18. Bisplinghoff, R.L., Ashley, H. and Halfman, R.L. Aeroelasticity, Dover Publications., New York, USA, 1996 Google Scholar
19. Megson, T.H.G. Aircraft Structures for Engineering Students, Butterworth-Heinemann, Burlington (MA), 2003, 3rd ed.Google Scholar
20. MSCMDNASTRAN®, Software Package, Ver. R3-2006, Reference Manual.Google Scholar
21. Broadbent, E.G. Flutter and Response Calculations in Practice, AGARD Manual on Aeroelasticity, 3, NASA, February 1963.Google Scholar
22. Pecora, R., Pecora, M. and Lecce, L. Flutter Certifcation of SKYCAR Aircraft: Rational Analysis and Flight Tests, Proceedings of the 3rd CEAS Air&Space Conference, Venice, Italy, September 2011.Google Scholar