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Improving wing aeroelastic characteristics using periodic design

  • Badran, Hossam T. (Aerospace Engineering Department, Cairo University) ;
  • Tawfik, Mohammad (Aerospace Engineering, University of Science and Technology, Zewail City for Science and Technology) ;
  • Negm, Hani M. (Aerospace Engineering Department, Cairo University)
  • Received : 2016.08.17
  • Accepted : 2017.02.11
  • Published : 2017.07.25
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Abstract

Flutter is a dangerous phenomenon encountered in flexible structures subjected to aerodynamic forces. This includes aircraft, buildings and bridges. Flutter occurs as a result of interactions between aerodynamic, stiffness, and inertia forces on a structure. In an aircraft, as the speed of the flow increases, there may be a point at which the structural damping is insufficient to damp out the motion which is increasing due to aerodynamic energy being added to the structure. This vibration can cause structural failure, and therefore considering flutter characteristics is an essential part of designing an aircraft. Scientists and engineers studied flutter and developed theories and mathematical tools to analyze the phenomenon. Strip theory aerodynamics, beam structural models, unsteady lifting surface methods (e.g., Doublet-Lattice) and finite element models expanded analysis capabilities. Periodic Structures have been in the focus of research for their useful characteristics and ability to attenuate vibration in frequency bands called "stop-bands". A periodic structure consists of cells which differ in material or geometry. As vibration waves travel along the structure and face the cell boundaries, some waves pass and some are reflected back, which may cause destructive interference with the succeeding waves. This may reduce the vibration level of the structure, and hence improve its dynamic performance. In this paper, for the first time, we analyze the flutter characteristics of a wing with a periodic change in its sandwich construction. The new technique preserves the external geometry of the wing structure and depends on changing the material of the sandwich core. The periodic analysis and the vibration response characteristics of the model are investigated using a finite element model for the wing. Previous studies investigating the dynamic bending response of a periodic sandwich beam in the absence of flow have shown promising results.

Keywords

References

  1. Abramovich, H. (1998), "Deflection control of laminated composite beam with piezoceramic layers-closed form solutions", Compos. Struct., 43(3), 217-231. https://doi.org/10.1016/S0263-8223(98)00104-4
  2. Aldraihem, O.J. and Khdeir, A.A. (2000), "Smart beams with extension and thickness-shear piezoelectric actuators", Smart Mater. Struct., 9(1), 1-9. https://doi.org/10.1088/0964-1726/9/1/301
  3. Aldraihem, O.J., Wetherhold, R.C. and Singh, T. (1997), "Distributed control of laminated beams: Timoshenko vs. Euler-Bernoulli theory", J. Intell. Mater. Syst. Struct., 8(2), 149-157. https://doi.org/10.1177/1045389X9700800205
  4. Badran, H.T. (2008a), "Vibration attenuation of periodic sandwich beams", M.S. Dissertation, Cairo University, Egypt.
  5. Badran, H.T., Tawfik, M. and Negm, H.M. (2008b), "Vibration characteristics of periodic sandwich beams", Proceedings of the 13th International Conference on Applied Mechanics and Mechanical Engineering, Cairo, Egypt.
  6. Bannerjee, J.R. (1999), "Explicit frequency equation and mode shapes of a cantilever beam coupled in bending and torsion", J. Sound Vibr., 224(2), 267-281. https://doi.org/10.1006/jsvi.1999.2194
  7. Benjeddou, A., Trindade, M.A. and Ohayon, R. (1999), "New shear actuated smart structure beam finite element", Am. Inst. Aeronaut. Astronaut. J., 37(3), 378-383. https://doi.org/10.2514/2.719
  8. Bisplinghoff, R.L., Ashley, H. and Halfman, R.L. (1996), Aeroelasticity, Dover Publishers, New York, U.S.A.
  9. Chandrashekhara, K. and Varadarajan, S. (1997), "Adaptive shape control of composite beams with piezoelectric actuators", J. Intell. Mater. Syst. Struct., 8(2), 112-124. https://doi.org/10.1177/1045389X9700800202
  10. Crawley, E.F. and De Luis, J. (1987), "Use of piezoelectric actuators as elements of intelligent structures", Am. Inst. Aeronaut. Astronaut. J., 25(10), 1373-1385. https://doi.org/10.2514/3.9792
  11. Daniel, M.D., Carlos, E.S., Jun, S.O. and Roberto, G.A. (2010), "Aeroelastic tailoring of composite plates through eigenvalues optimization", Assoc. Argent. Mecan. Comput., XXIX, 609-623.
  12. Donthireddy, P. and Chandrashekhara, K. (1996), "Modelling and shape control of composite beam with embedded piezoelectric actuators", Compos. Struct., 35(2), 237-244. https://doi.org/10.1016/0263-8223(96)00041-4
  13. Faulkner, M.G. and Hong, D.P. (1985), "Free vibration of mono-coupled periodic system", J. Sound Vibr., 99(1), 29-42. https://doi.org/10.1016/0022-460X(85)90443-2
  14. Georghiades, G.A. and Banerjee, J.R. (1997), "Flutter prediction for composite wings using parametric studies", Am. Inst. Aeronaut. Astronaut. J., 35(4), 746-748. https://doi.org/10.2514/2.170
  15. Goland, M. and Buffalo, N.Y. (1945), "The flutter of a uniform cantilever wing", J. Appl. Mech., 12(4), 197-208.
  16. Guertin, M.L. (2012), "The application of finite element methods to aeroelastic lifting surface flutter", M.S. Dissertation, Rice University, Houston, Texas, U.S.A.
  17. Guo, S.J. (2007), "Aeroelastic optimization of an aerobatic aircraft wing structure", Aerosp. Sci. Technol., 11(5), 396-404. https://doi.org/10.1016/j.ast.2007.01.003
  18. Guo, S.J., Bannerjee, J.R. and Cheung, C.W. (2003), "The effect of laminate lay-up on the flutter speed of composite wings", J. Aerosp. Eng., 207(3), 115-122.
  19. Gupta, G.S. (1970), "Natural flexural waves and the normal modes of periodically-supported beams and plates", J. Sound Vibr., 13(1), 89-101. https://doi.org/10.1016/S0022-460X(70)80082-7
  20. Hollowell, S.J. and Dugundji, J. (1984), "Aeroelastic flutter and divergence stiffness coupled, graphite/epoxy cantilevered plates", J. Aircr., 21(1), 69-76. https://doi.org/10.2514/3.48224
  21. Kameyama, M. and Fukunaga, H. (2007), "Optimum design of composite plate wings for aeroelastic characteristics using lamination parameters", Comput. Struct., 85(3-4), 213-224. https://doi.org/10.1016/j.compstruc.2006.08.051
  22. Langley, R.S. (1996), "A transfer matrix analysis of the energetics of structural wave motion and harmonic vibration", Proceedings of the Royal Society A: Mathematical, Physical and Engineering Sciences, 452, 1631-1648. https://doi.org/10.1098/rspa.1996.0087
  23. Majid, D.L. and Basri, S. (2008), "LCO flutter of cantilevered woven 10 glass/epoxy laminate in subsonic flow", Acta Mech. Sinica., 24(1), 107-110. https://doi.org/10.1007/s10409-007-0117-y
  24. Manjunath, T.C. and Bandyopadhyay, B. (2005), "Modelling and fast output sampling feedback control of a smart Timoshenko cantilever beam", J. Smart Struct. Syst., 1(3), 283-308. https://doi.org/10.12989/sss.2005.1.3.283
  25. Mead, D.J. (1996), "Wave propagation in continuous periodic structures: Research contributions from Southampton, 1964-1995", J. Sound Vibr., 190(3), 495-524. https://doi.org/10.1006/jsvi.1996.0076
  26. Mead, D.J. and Parathan, S. (1979), "Free wave propagation in two dimensional periodic plates", J. Sound Vibr., 64(3), 325-348. https://doi.org/10.1016/0022-460X(79)90581-9
  27. Mead, D.J. and Yaman, Y. (1991), "The response of infinite periodic beams to point harmonic forces: A flexural wave analysis", J. Sound Vibr., 144(3), 507-530. https://doi.org/10.1016/0022-460X(91)90565-2
  28. Reddy, J.N. (2002), Energy Principles and Variational Methods in Applied Mechanics, John Willy & Sons, New Jersey, U.S.A.
  29. Thomas, J. and Abbas, B.A. (1975), "Finite element methods for dynamic analysis of Timoshenko beam", J. Sound Vibr., 41, 291-299. https://doi.org/10.1016/S0022-460X(75)80176-3
  30. Trindade, M.A., Benjeddou, A. and Ohayon, R. (1999), "Parametric analysis of the vibration control of sandwich beams through shear-based piezoelectric actuation", J. Intell. Mater. Syst. Struct., 10(5), 377-385. https://doi.org/10.1177/1045389X9901000503
  31. Ungar, E.E. (1966), "Steady-state response of one-dimensional periodic flexural systems", J. Acoust. Soc. Am., 39(5), 887-894. https://doi.org/10.1121/1.1909967
  32. Zhang, X. and Sun, C. (1996), "Formulation of an adaptive sandwich beam", Smart Mater. Struct., 5(6), 814-823. https://doi.org/10.1088/0964-1726/5/6/012