Finite element nonlinear panel flutter with arbitrary temperatures in supersonic flow

Thermal Stability Characteristics and Limit Cycle Oscillation of Smart Skin Structures

“…As the ratio is increased, the critical aerodynamic pressure is increased. The reason is that the airflows affect equally along the x-direction for these cases, and similar results are discussed in reference [21]. Additionally, difference of the critical aerodynamic pressures between the models is decreased according to the temperature rises.…”

“…Also, g a , 0 , A f and A d are the non-dimensional aerodynamic damping parameter, convenient reference frequency, the aerodynamic influence matrix and aerodynamic damping matrix, respectively [21].…”

Thermal post-buckling and flutter characteristics of composite plates embedded with shape memory alloy fibers

“…Xue and Mei [1,2] researched the nonlinear panel flutter and fatigue with arbitrary temperature changes. In the research, the isotropic plate was used, and the finite element method based on the classical plate theory was adopted.…”

Application of aeroelastic modes on nonlinear supersonic panel flutter at elevated temperatures

“…With the use of von Kármán plate theory, the maximum deflection is of order of plate thickness. The finite element system equations of motion for nonlinear flutter of a laminated composite panel at an arbitrary yawed supersonic flow angle K and temperature distribution DT can be expressed in the matrix form [2,[4][5][6][8][9][10][11][12][13] as The parameters k, C a and K are the non-dimensional dynamic pressure, non-dimensional aerodynamic damping, and flow yaw angle, respectively, with k and C a defined as [4,10] k ¼ 2q a a 3 bD 110…”