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TECHNICAL PAPERS

Analysis of Nonlinear Aeroelastic Panel Response Using Proper Orthogonal Decomposition

[+] Author and Article Information
Sean A. Mortara, Joseph Slater

Dept. of Mech. & Mat. Engr., Wright State University, Dayton, Ohio 45435 (937)-775-5085

Philip Beran

Air Force Research Laboratory, VASD, Wright-Patterson AFB, Dayton, Ohio 45433e-mail: philip.beran@wpafb.af.mil

J. Vib. Acoust 126(3), 416-421 (Jul 30, 2004) (6 pages) doi:10.1115/1.1687389 History: Received September 01, 2001; Revised July 01, 2003; Online July 30, 2004
Copyright © 2004 by ASME
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References

Dowell,  E. H., 1966, “Nonlinear Oscillations of a Fluttering Plate,” AIAA J., 4(7), July, pp. 1267–1275.
Dowell, E. H., 1975, Aeroelasticity of Plates and Shells, chap. 3: “Nonlinear Theoretical Aeroelastic Models,” pp. 35–36.
Slater,  J., Petit,  C., and Beran,  P., 2002, “In-Situ Subspace Evaluation in Reduced Order Modeling,” Shock Vib., 9, pp. 105–122.
Beran, P., and Silva, W., 2001, “Reduced-Order Modeling: New Approaches for Computational Physics,” 39th Aerospace Sciences Meeting & Exhibit, No. 2001-0853, Reno, NV, Jan 2001.
Romanowski, M., 1996, “Reduced Order Unsteady Aerodynamic and Aeroelastic Models Using Karhunen-Loeve Eigenmodes,” Part 3, Bellevue, WA, Sept., AIAA 96-3981-CP.
Holmes, P., Lumley, J., and Berkooz, G., 1996, Turbulence, Coherent Structures, Dynamical Systems and Symmetry, Cambridge University Press.
Park,  H., and Lee,  M., 1998, “An Efficient Method for Solving the Navier-Stokes Equations for Flow Control,” Int. J. Numer. Methods Eng., 41, pp. 1133–1151.
Hall, K., Thomas, J., and Dowell, E., 1999, “Reduced-Order Modeling of Unsteady Small-Disturbance Flows Using a Frequency-Domain Proper Orthogonal Decomposition Technique,” No. 0655, Jan.
Beran, P., and Petit, C., 2001, “Prediction of Nonlinear Panel Response Using Proper Orthogonal Decomposition,” 42nd Structures, Structural Dynamics, and Materials Conference, No. 2001-1292, Seattle, WA, Apr.
Krysl,  P., Lall,  S., and Marsden,  J., 2001, “Dimensional Model Reduction in Non-Linear Finite Element Dynamics of Solids and Structures,” Int. J. Numer. Methods Eng., 51(4), pp. 479–504.
Mortara, S. A., Slater, J. C., and Beran, P. S., 2000, “A Proper Orthogonal Decomposition Technique for the Computation of Nonlinear Panel Response,” 41st Structures, Structural Dynamics, and Materials Conference, No. 2000-1936, Atlanta, GA, Apr.
Beran, P., Huttsel, L., and Buxton, B., 1999, “Computational Aeroelasticity Techniques for Viscous Flow,” CEAS/AIAA/CASE/NASA Langley International Forum on Aeroelasticity and Structural Dynamics, Williamsburg, Virginia, June.
Selvam, R., and Visbal, M., 1998, “Computation of Nonlinear Viscous Panel Flutter Using a Fully-Implicit Aeroelastic Solver,” Long Beach, CA, April, AIAA-98-1844.
Selvam, R., 1998, “Computer Modeling of Nonlinear Viscous Panel Flutter,” Tech. rep., ARFL, WPAFB, OH, August.
O’Callahan, J., Avitabile, P., and Riemer, R., 1989, “System Equivalent Reduction Expansion Process (SEREP),” Proceedings of the 7th International Modal Analysis Conference, Las Vegas, Nevada, February.
Inman, D. J., 1996, Engineering Vibration, Prentice Hall Chap. 4.3.

Figures

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1-D panel subject to high speed flow
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First 4 dominant modes of an aeroelastic panel
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Full-Order time deflection showing captured training period (ξ=0.75)
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Comparison of 2, 3, and 4 mode ROM
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LCO amplitude comparison of 3 and 4 Mode ROM
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Limit cycle study with different μ/M
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Stability boundary for varying in-plane loads

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