International Journal of Aerospace Engineering / 2015 / Article / Fig 4

Research Article

Nonlinear Vibrations of FGM Cylindrical Panel with Simply Supported Edges in Air Flow

Figure 4

The periodic response of the FGM cylindrical panel occurs when the magnitude of the in-plane excitation is taken to be . The volume fraction index is taken to be 0.5. The Mach number is taken to be 5.0. (a) The phase portrait on plane (); (b) the time response on the planes (); (c) the phase portrait on plane (); (d) the responses on the planes (); (e) three-dimensional phase portrait in space (); (f) the Poincare section on plane ().
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