Nonlinear response of composite panels under combined acoustic excitation and aerodynamic pressure

Abstract

J/j_aA finite element formulation is presented for the analysis of large deflection response of composite panels subjected to aerodynamic pressure at supersonic flow and high acoustic excitation. The first-order shear deformation theory is considered for laminated composite plates, and the von Karman nonlinear straindisplacement relations are employed for the analysis of large deflection panel response. The first-order piston theory aerodynamics and the simulated Gaussian white noise are employed for the aerodynamic and acoustic loads, respectively.The nonlinear equations of motion for an arbitrarily laminated composite panel subjected to a combined aerodynamic and acoustic pressures are formulated first in structure node degrees-of-freedom. The system equations are then transformed and reduced to a set of coupled nonlinear equations in modal coordinates. Modal participation is defined and the in-vacuo modes to be retained in the analysis are based on the modal participation values. Numerical results include root mean square values of maximum deflections, deflection and strain response time histories, probability distributions, and power spectrum densities. Results showed that combined acoustic and aerodynamic loads have to be considered for panel analysis and design at high dynamic pressure values.

Thermoacoustic Random Response of Shape Memory Alloy Hybrid Composite Plates

“…(11) will not bring significant error, because their natural frequencies are usually two to three orders of magnitude higher than those of bending [16].…”

“…Locke [15] investigated the large deflection random vibration of a thermally buckled thin isotropic plate using the method of equivalent linearization and assuming temperature-independent material properties. Abdel-Motagaly et al [16] adopted finite element numerical integration to study the nonlinear panel response of thick composite-plate panels under combined aerodynamic and acoustic loads. Dhainaut et al [17,18] presented a finite element solution for the prediction of nonlinear random response of thin isotropic and composite panels subjected to the simultaneous action of band-limited white-Gaussian noise and elevated temperatures.…”

Supersonic flutter of laminated composite panel in coupled multi-fields

“…In the present study, mode shapes, which satisfy the boundary conditions shown in Eq. (14), are assumed to be…”

“…Motagaly et al [14] gave the response of nonlinear panels subjected to combined acoustic and aerodynamic pressures using finite element method. The simulation indicated that the acoustic pressure should be considered for λ > λ cr .…”

Random Response of Shape Memory Alloy Hybrid Composite Plates Subject to White-Gaussian Noise and Thermal Environment

“…Locke [10] investigated the large deflection random vibration of a thermally buckled thin isotropic plate, using the method of equivalent linearization, while assuming a temperature-independent material properties. Abdel-Motagaly et al [11] used finite element numerical integration to study nonlinear panel response under combined aerodynamic and acoustic loads. Dhainaut et al [12] and [13] presented a finite element formulation for the prediction Shape memory alloys (SMAs) have a unique ability to completely recover large prestrains (up to 10%) when heated above certain characteristic temperature called the austenite finish temperature.…”