Hostname: page-component-586b7cd67f-l7hp2 Total loading time: 0 Render date: 2024-11-25T02:01:53.584Z Has data issue: false hasContentIssue false
  • English
  • Français

Non-linear aeroelastic response of high aspect-ratio wings in the frequency domain

Published online by Cambridge University Press:  11 May 2017

F. Afonso ,
J. Vale ,
É. Oliveira ,
F. Lau  and
A. Suleman
F. Afonso
Affiliation:
CCTAE, IDMEC, Instituto Superior Técnico, Universidade de Lisboa, Lisboa, Portugal
J. Vale
Affiliation:
CCTAE, IDMEC, Instituto Superior Técnico, Universidade de Lisboa, Lisboa, Portugal
É. Oliveira
Affiliation:
CCTAE, IDMEC, Instituto Superior Técnico, Universidade de Lisboa, Lisboa, Portugal
F. Lau
Affiliation:
CCTAE, IDMEC, Instituto Superior Técnico, Universidade de Lisboa, Lisboa, Portugal
A. Suleman*
Affiliation:
CCTAE, IDMEC, Instituto Superior Técnico, Universidade de Lisboa, Lisboa, Portugal
*
*Corresponding author. Also Department of Mechanical Engineering, University of Victoria, Victoria, BC, Canada. suleman@uvic.ca
Get access Rights & Permissions [Opens in a new window]

Abstract

A current trend in the aeronautic industry is to increase the wing aspect ratio to enhance aerodynamic efficiency by reducing the induced drag and thus reduce fuel consumption. Despite the associated benefits of a large aspect ratio, such as higher lift-to-drag ratios and range, commercial aircraft usually have a relatively low aspect ratio. This is partially explained by the fact that the wing becomes more flexible with increasing aspect ratio and thus more prone to large deflections, which can cause aeroelastic instability problems such as flutter. In this work, an aeroelastic study is conducted on a rectangular wing model of 20 m span and variable chord for a low subsonic speed condition to evaluate the differences between linear and non-linear static aeroelastic responses. Comparisons between linear and non-linear displacements, natural frequencies and flutter boundary are performed. An in-house non-linear aeroelastic framework was employed for this purpose. In this work, the influence of the aspect ratio and geometric non-linearity (highly deformed states) is assessed in terms of aeroelastic performance parameters: flutter speed and divergence speed. A nearly linear correlation of flutter speed difference (relative to linear analysis results) with vertical-tip displacement difference is observed. The flutter and divergence speeds vary substantially as the wing aspect ratio increases, and the divergence speeds always remain above the flutter speed. Furthermore, the flutter mechanism was observed to change as the wing chord is decreased.

Type
Research Article
Information
The Aeronautical Journal , Volume 121 , Issue 1240 , June 2017 , pp. 858 - 876
Copyright
Copyright © Royal Aeronautical Society 2017 

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

REFERENCES

1. Abbas, A., de Vicente, J. and Valero, E. Aerodynamic technologies to improve aircraft performance, Aerospace Science and Technology, 2013, 28, pp 100-132.CrossRefGoogle Scholar
2. Abbott, I.H. and Doenhoff, A.E.V. Theory of Wing Sections, Including a Summary of Airfoil Data, 1959, Dover Publications, New York, US.Google Scholar
3. Afonso, F., Leal, G., Vale, J., Oliveira, É., Lau, F. and Suleman, A. The effect of stiffness and geometric parameters on the nonlinear aeroelastic performance of high aspect ratio wings, Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2016. Available at: http://dx.doi.org/10.1177/0954410016675893 Google Scholar
4. Albano, E. and Rodden, W.P. A doublet-lattice method for calculating lift distributions on oscillating surfaces in subsonic flows, AIAA J, February 1969, 7, (2), pp 279-285.Google Scholar
5. Arena, A., Lacarbonara, W. and Marzocca, P. Nonlinear aeroelastic formulation for flexible high-aspect ratio wings via geometrically exact approach, Proceedings of 52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, 2011, Denver, Colorado, US.Google Scholar
6. Ballmann, J. (Ed) Flow Modulation and Fluid—Structure Interaction at Airplane Wings, Notes on Numerical Fluid Mechanics and Multidisciplinary Design, volume 84, 1 ed, 2003, Springer, Berlin, Germany.Google Scholar
7. Bazilevs, Y., Takizawa, K. and Tezduyar, T.E. Computational Fluid-Structure Interaction: Methods and Applications, Wiley Series in Computational Mechanics, 1st ed, 2013, John Wiley & Sons, Ltd, New York, US.Google Scholar
8. Bertin, J.J. Aerodynamics for Engineers, 4th ed, 2002, Prentice Hall, New Jersey, US.Google Scholar
9. Bhatia, K.G. Airplane aeroelasticity: Practice and potential, J Aircr, 2003, 40, (6), pp 1010-1018.Google Scholar
10. Carrier, G., Atinault, O., Dequand, S., Hantrais-Gervois, J.-L., Liauzun, C., Paluch, B., Rodde, A.-M. and Toussaint, C. Investigation of a strut-braced wing configuration for future commercial transport, Proceedings of 28th International Congress of the Aeronautical Sciences, 2012, Brisbane, Australia.Google Scholar
11. Cavallaro, R. and Demasi, L. Challenges, ideas, and innovations of joined-wing configuration: A concept from the past, and opportunity for the future, Progress in Aerospace Sciences, 2016, 87, pp 1-93.Google Scholar
12. Cesnik, C.E.S. and Brown, E.L. Modeling of a high aspect ratio active flexible wings for roll control, Proceedings of 43rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2002, Denver, Colorado, US.Google Scholar
13. Cesnik, C.E.S. and Su, W. Nonlinear aeroelastic modeling and analysis of fully flexible aircraft, Proceedings of 46th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2005, Austin, Texas, US.Google Scholar
14. Demasi, L., Monegato, G., Dipace, A. and Cavallaro, R. Minimum induced drag theorems for joined wings, closed systems, and generic biwings: Theory, J Optimization Theory and Applications, 169, (1), 200-235, 2016.CrossRefGoogle Scholar
15. Demasi, L., Monegato, G., Rizzo, E., Cavallaro, R. and Dipace, A. Minimum induced drag theorems for joined wings, closed systems, and generic biwings: Applications, J Optimization Theory and Applications, 169, (1), 236-261, 2016.Google Scholar
16. Dowell, E.H. and Tang, D. Effects of geometric structural nonlinearity on flutter and limit cycle oscillations of high-aspect-ratio wings, J Fluid and Structure, 2004, 19, pp 291-306.Google Scholar
17. Drela, M. Integrated simulation model for preliminary aerodynamic, structural, and control-law design of aircraft, Proceedings of 40th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, Saint Louis, Missouri, US, 1999. AIAA Paper 99-1394.Google Scholar
18. Dunn, P. and Dugundji, J. Nonlinear stall flutter and divergence analysis of cantilevered graphit/epoxy wings, AIAA J, 1992, 30, (1), pp 153-162.Google Scholar
19. Frediani, A., Cipolla, V. and Rizzo, E. The PrandtlPlane Configuration: Overview on Possible Applications to Civil Aviation, 2012, Springer, Boston, Massachusetts, US, pp 179-210.Google Scholar
20. Harmin, M.Y. and Cooper, J.E. Aeroelastic behaviour of a wing including geometric nonlinearities, Aeronautcial J, December 2011, 115, (1174), Pp 767-777.Google Scholar
21. Hodges, D.J. and Pierce, G.A. Introduction to Structural Dynamics and Aeroelasticity. 1996, Press Syndicate of the University of Cambridge, Cambridge, UK.Google Scholar
22. Hulshoff, S. Aeroelasticity course, 2011. University of Delft, Course Notes.Google Scholar
23. Kampchen, M., Dafnis, A., Reimerdes, H., Britten, G. and Ballmann, J. Dynamic aero-structural response of an elastic wing model, J Fluid and Structure, 2003, 18, pp 63-77.Google Scholar
24. Katz, J. and Plotkin, A. Low-speed Aerodynamics, 2001, Cambridge University Press, New York, US.Google Scholar
25. Mason, W.H. Program FRICTION - virginia tech aerospace engineering aerodynamics and design software collection, Tech Rep, 2006, Department of Aerospace and Ocean Engineering, Virginia Polytechnic Institute and State University, Blacksburg, Virginia, US.Google Scholar
26. McMasters, J.H. and Kroo, I.M. Advanced configurations for very large transport airplanes, Aircr Design, 1998, 1, (4), pp 217-242.Google Scholar
27. Murua, J. Flexible Aircraft Dynamics with a Geometrically-Nonlinear Description of the Unsteady Aerodynamics, PhD Thesis, May 2012, Department of Aeronautics, Imperial College London, London, UK.Google Scholar
28. Murua, J., Palacios, R. and Graham, J.M.R. Applications of the unsteady vortex-lattice method in aircraft aeroelasticity and flight dynamics, Progress in Aerospace Sciences, 2012, 55, pp 46-72.Google Scholar
29. Patil, M.J. Nonlinear gust response of highly flexible aircraft, Proceedings of 48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, 2007.Google Scholar
30. Patil, M.J. and Hodges, D.H. On the importance of aerodynamic and structural geometrical nonlinearities in aeroelastic behavior of high-aspect-ratio wing, J Fluid and Structure, 2004, 19, pp 905-915.Google Scholar
31. Patil, M.J. and Hodges, D.H. Flight dynamics of highly flexible flying wings, J Aircr, 2006, 43, (6), pp 1790-1799.Google Scholar
32. Patil, M.J., Hodges, D.H. and Cesnik, C.E.S. Nonlinear aeroelasticity and flight dynamics of high-altitude long-endurance aircraft, J Aircr, 2001, 38, (1), pp 88-94.Google Scholar
33. Patil, M. J., Hodges, D.H. and Cesnik, C.E.S. Limit-cycle oscillations in high-aspect-ratio wings, J Fluids and Structures, 2001, 15, (1), pp 107-132.Google Scholar
34. Shearer, C. M. and Cesnik, C.E.S. Nonlinear flight dynamics of very flexible aircraft, J Aircr, 2007, 44, (5), pp 1528-1545.Google Scholar
35. Suleman, A., Afonso, F., Vale, J., Oliveira, É. and Lau, F. Non-linear aeroelastic analysis in the time domain of high-aspect-ratio wings: Effect of chord and taper-ratio variation, Aeronautical J, 2017, 121, (1235), pp 21-53.CrossRefGoogle Scholar
36. Tang, D. and Dowell, E.H. Experimental and theoretical study on aeroelastic response of high-aspect-ratio wings, AIAA J, 2001, 39, (8), pp 1430-1441.Google Scholar
37. Tang, D. and Dowell, E.H. Experimental and theoretical study of gust response for high-aspect-ratio wing, AIAA J, 2002, 40, (3), pp 419-429.Google Scholar
38. Wang, Z., Chen, P., Liu, D. and Mook, D. Nonlinear-aerodynamic/nonlinear-structure interaction methodology for a high-altitude-long-endurance wing, J Aircr, 2010, 47, (2), pp 556-566.Google Scholar
39. Wolkovitch, J. The joined wing: An overview, J Aircr, 1986, 23, (3), pp 161-178.Google Scholar
40. Wright, J.R. and Cooper, J.E. Introduction to Aircraft Aeroelasticity and Loads, 2007, Aerospace Series. John Wiley & Sons, Ltd, Chichester, UK.Google Scholar
41. Zienkiewicz, O.C. The Finite Element Method in Engineering Science, 3rd ed., 1977, McGraw-Hill, London, UK.Google Scholar