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Abstract The nonlinear flutter responses of heated panels in supersonic airflow are studied. The aeroelastic model of three-dimensional panels considering thermal effect is established by the use of von Karman large deflection strain-displacement formulations, quasi-steady first-order piston theory aerodynamics and the principle of virtual work. The governing equations in structural node degree of freedom are expressed in the function of linear modal coordinates. The amplitude and frequency of panel flutter response is obtained using both frequency domain method and time domain numerical integration. The numerical results show that the time domain method is consistant with the frequency domain method when panel flutter response is simply harmonic limit cycle oscillation.
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Received: 03 November 2009
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2010, Vol. 31 
