Aerothermoacoustic Response of Shape Memory Alloy Hybrid Composite Panels

초록

Supersonic nonlinear vibrations of a traditional composite panel impregnated with prestrained shape memory alloy fibers and subjected to combined aerodynamic, thermal, and random acoustic loads are investigated. A nonlinear finite element model is developed using the first-order shear-deformable plate theory, von Karman strain-displacement relations, and the principle of virtual work. The aerodynamic pressure is modeled using the quasi-steady first-order piston theory. Thermal load is assumed to be steady-state constant temperature distribution, and the acoustic excitation is considered to be a white-Gaussian random pressure with zero mean and uniform magnitude over the panel surface. Nonlinear temperature-dependence of material properties is considered in the formulation. The dynamic nonlinear equations of motion are transformed to modal coordinates to reduce the computational efforts. The Newton-Raphson iteration method is employed to obtain the dynamic response at each time step of the Newmark numerical integration scheme. Finally, the nonlinear response of a shape memory alloy hybrid composite panel is presented, illustrating the effect of shape memory alloy fiber embeddings, aerodynamic pressure, sound pressure level, and temperature rise on the panel response.

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