TY - GEN
T1 - Nonlinear aeroelastic panel flutter based on proper orthogonal decomposition
AU - Zhou, Jian
AU - Yang, Zhi Chun
PY - 2014
Y1 - 2014
N2 - It is commonly accepted that 36 in vacuo natural modes (NMS) are needed for converged, limit-cycle oscillations (LCOs) of isotropic or laminated anisotropic rectangular panels in supersonic air flow. It's computationally costly for nonlinear aeroelastic panel response using such a large number of modes, and it also causes complexity and difficultly in designing controllers for panel flutter suppression. Based on Hamilton principle, the aeroelastic finite element motion equations of the 3-D panel are established by using the von Karman large deflection theory, first-order piston theory aerodynamics, the proper orthogonal decomposition (POD) method are adopted to construct a reduced order model of the panel, then the reduced panel flutter equations are solved in time domain using a numerical integration method. Comparing with the LCOs calculated by using 36NMS, the results obtained by using the reduced order model based on POD method (POD/ROM) show a good agreement.
AB - It is commonly accepted that 36 in vacuo natural modes (NMS) are needed for converged, limit-cycle oscillations (LCOs) of isotropic or laminated anisotropic rectangular panels in supersonic air flow. It's computationally costly for nonlinear aeroelastic panel response using such a large number of modes, and it also causes complexity and difficultly in designing controllers for panel flutter suppression. Based on Hamilton principle, the aeroelastic finite element motion equations of the 3-D panel are established by using the von Karman large deflection theory, first-order piston theory aerodynamics, the proper orthogonal decomposition (POD) method are adopted to construct a reduced order model of the panel, then the reduced panel flutter equations are solved in time domain using a numerical integration method. Comparing with the LCOs calculated by using 36NMS, the results obtained by using the reduced order model based on POD method (POD/ROM) show a good agreement.
KW - LCO
KW - Nonlinear aeroelasticity
KW - Panel flutter
KW - Proper orthogonal decomposition (POD)
UR - http://www.scopus.com/inward/record.url?scp=84892178098&partnerID=8YFLogxK
U2 - 10.4028/www.scientific.net/AMM.482.42
DO - 10.4028/www.scientific.net/AMM.482.42
M3 - 会议稿件
AN - SCOPUS:84892178098
SN - 9783037859858
T3 - Applied Mechanics and Materials
SP - 42
EP - 48
BT - Structural Engineering, Vibration and Aerospace Engineering
T2 - 2013 International Conference on Structural Engineering, Vibration and Aerospace Engineering, SEVAE 2013
Y2 - 23 November 2013 through 24 November 2013
ER -