Sound Radiation and Vibration of Composite Panels Excited by Turbulent Flow: Analytical Prediction and Analysis

Abstract

The present study investigates the vibration and sound radiation by panels exited by turbulent flow and by random noise. Composite and aluminum panels are analyzed through a developed analytical framework. The main objective of this study is to identify the difference between the vibroacoustic behaviour of these two types of panels. This topic is of particular importance, given the growing interest in applying composite materials for the construction of aircraft structures, in parts where aluminum panels were traditionally being used. An original mathematical framework is presented for the prediction of noise and vibration for composite panels. Results show the effect of panel size, thickness of core, and thickness of face layers on the predictions. Smaller composite panels generally produced lower levels of sound and vibration than longer and wider composite panels. Compared with isotropic panels, the composite panels analyzed generated lower noise levels, although it was observed that noise level was amplified at certain frequencies.

Sound transmission through double cylindrical shells lined with porous material under turbulent boundary layer excitation

“…Many researchers in the past have paid attention to the noise radiated by a single plate [17][18][19][20][21][22][23][24][25]. However, these studies are still quite far away from real industrial problems.…”

Experimental and numerical characterization of a ceramic matrix composite shroud segment under impact loading

“…The development of new materials-such as composite materials-has paved the way for significant mass reduction in aerospace structural components [1]. The use of such materials is indeed increasingly common for aircraft structures and even aircraft engines as they are typically found in the fan stage [7,8], acoustic lining panels [9,10,11] as well as various components of the nacelle [12,13]. However, the use of composite materials within the hot sections of an aircraft engine remains a challenge for engineers due to extreme thermal conditions.…”

Reproducing Acceleration Power Spectral Density from an Aircraft Fuselage Panel Excited by Turbulent Boundary Layer Using Piezoelectric Actuators

“…Therefore, when looking at simple shapes, like that of a flat panel, analytical computational methods become a better choice. The analytical expressions for RSP can be derived for a given aircraft panel, in terms of the displacement PSD [1,17,18]. The acceleration PSD is calculated from the displacement PSD, which is proportional to the RSP [18].…”

“…The analytical expressions for RSP can be derived for a given aircraft panel, in terms of the displacement PSD [1,17,18]. The acceleration PSD is calculated from the displacement PSD, which is proportional to the RSP [18]. The analytical models developed, by Rocha, were modified to account for other panel and enclosure combinations [19,20].…”

“…For the TBL excitation the autocorrelation is used and for the point force and the piezoelectric patch excitations the cross spectrum correlation is used. The equations required to calculate the velocity, S , and the acceleration PSD, S AA , at a single point on the panel are as follows [18]:…”