CFD-based Analysis of Aeroelastic behavior of Supersonic Fins
Автор: Tianxing Cai, Min Xu, Weigang Yao
Журнал: International Journal of Intelligent Systems and Applications(IJISA) @ijisa
Статья в выпуске: 1 vol.3, 2011 года.
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The main goal of this paper is to analyze the flutter boundary, transient loads of a supersonic fin, and the flutter with perturbation. Reduced order mode (ROM) based on Volterra Series is presented to calculate the flutter boundary, and CFD/CSD coupling is used to compute the transient aerodynamic load. The Volterra-based ROM is obtained using the derivative of unsteady aerodynamic step-response, and the infinite plate spline is used to perform interpolation of physical quantities between the fluid and the structural grids. The results show that inertia force plays a significant role in the transient loads, the moment cause by inertia force is lager than the aerodynamic force, because of the huge transient loads, structure may be broken by aeroelasticity below the flutter dynamic pressure. Perturbations of aircraft affect the aeroelastic response evident, the reduction of flutter dynamic pressure by rolling perturbation form 15.4% to 18.6% when Mach from 2.0 to 3.0. It is necessary to analyze the aeroelasticity behaviors under the compositive force environment.
Aeroelasticity, flutter boundary, transient loads, CFD/CSD, ROM
Короткий адрес: https://sciup.org/15010152
IDR: 15010152
Список литературы CFD-based Analysis of Aeroelastic behavior of Supersonic Fins
- Sorin Munteanu, John Rajadas. A Volterra Kernel Reduced-Order Model Approach for Nonlinear Aeroelastic Analysis [C]. AIAA 2005-1854.
- Yao Weigang, Xu Min. Aeroelasticity Numerical Analysis Via Volterra Series Approach [J]. Journal of Astronautics, 2008, 29(6): 1711-1716. (in Chinese)
- N.V. Taylor, C.B. Allen, A. Gaitonde, Moving Mesh CFD-CSD Aeroservoelastic Modelling of BACT Wing with Autonomous Flap Control, AIAA 2005-4840.
- Asitav Mishra, Shreyas Ananthan, James D. Baeder, Coupled CFD/CSD Prediction of the Effects of Trailing Edge Flaps on Rotorcraft Dynamic Stall Alleviation, AIAA 2009-891.
- W.A. Silva, Identification of Linear and Nonlinear Aerodynamic Impulse Responses Using Digital Filter Techniques, AIAA Paper No. 97-3712.
- David J. Lucia, Philip S. Beran, Walter A. Silva, Aeroelastic System Development Using Proper Orthogonal Decomposition and Volterra Theory, AIAA 2003-1922.
- Satish K. Chimakurthi, Bret K. Stanford, Carlos E. S. Cesnik, Flapping Wing CFD/CSD Aeroelastic Formulation Based on a Corotational Shell Finite Element, AIAA 2009-2412.
- Haroon A. Baluch, P. Lisandrin, R. Slingerland, and M. J. L. Van Tooren, Effects of Flexibility on Aircraft Dynamic Loads and Structural Optimization, AIAA 2007-768.
- Badcock, K. J., Woodgate, M. A. and Richards, B. E., "Direct aeroelastic bifurcation analysis of a symmetric wing based on the Euler equations", Technical Report 0315, Department of Aerospace Engineering, University of Glasgow, 2003.
- Parker G H. Dynamic Aeroelastic analysis of wing/store configurations. Doctor Thesis, Air Force Institute of Technology, 2005.
- Jack J. McNamara, Peretz P. Friedmann, Aeroelastic and Aerothermoelastic Analysis of Hypersonic Vehicles: Current Status and Future Trends, AIAA 2007-2013.
- Rodden W P, Johnson E H. MSC/NASTRAN Aeroelastic Analysis User’s Guide Version 68. The MacNeal-Schwendler Corp, 1994.
- XU Min LI Yong ZENG Xian-ang, Volterra-series-based reduced-order model for unsteady aerodynamics, Structure and environment engineering, Vol.34, No.5,p:22-28,2007.(in Chinese)
- Juang, J. N. and Pappa, R. S., An Eigensystem Realization Algorithm for Modal Parameter Identification and Model Reduction, Journal of Guidance, Vol. 8, No. 5, 1984, pp. 620-627.
- Y. Harmin1 and J.E. Cooper., Efficient Prediction of Aeroelastic Response Including Geometric Nonlinearities, AIAA 2010-2613.
