Noon Digital Resources
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Abstract
A new nonlinear finite element model is presented for the nonlinear
flutter response of moderately thick shape memory alloy hybrid composite
plate panels under the combined effect of thermal and aerodynamic loads. The
nonlinear governing equations of a moderately thick rectangular plate are
obtained using first-order shear-deformable plate theory (FSDT), von Karman
strain-displacement relations and the principle of virtual work. To account
for the temperature dependence of material properties, the thermal strain is
stated as an integral quantity of thermal expansion coefficient with respect
to temperature. The aerodynamic pressure is modeled using the quasi-steady
first-order piston theory. The Newton-Raphson iteration method is employed
to obtain the thermal post-buckling deflection, while the linearized updated
mode method is implemented in predicting the limit-cycle oscillation at
elevated temperatures. The numerical results show the thermal buckling and
flutter characteristics of shape memory alloy hybrid composites,
illustrating the effect of the SMA volume fraction and pre-strain value on
the aero-thermo-mechanical response of such plates.
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