Vibroacoustic Characterization of a New Hybrid Wing-Body Fuselage Concept

• Published in: NASA Center for AeroSpace Information (CASI). Misc. Resources
• Main Authors: Allen, Albert R, Przekop, Adam
• Format: Web Resource
• Language: English
• Published: Hampton NASA/Langley Research Center 09.08.2012
• Subjects: Acoustics; Aerodynamics; Aircraft compartments; Airframes; Commercial aircraft; Energy consumption; Finite element method; Fuselages; Mathematical models; Pressurized cabins; Robustness (mathematics); Sound waves; Statistical energy analysis; Substructures; Turbulent boundary layer

A lighter, more robust airframe design is required to withstand the loading inherent to next generation non cylindrical commercial airliners. The Pultruded Rod Stitched Efficient Unitized Structure concept, a highly integrated composite design involving a stitched and co-cured substructure, has been developed to meet such requirements. While this structure has been shown to meet the demanding out-of-plane loading requirements of the flat-sided pressurized cabin design, there are concerns that the stiff co-cured details will result in relatively high acoustic radiation efficiencies at frequencies well below the thin skin acoustic coincidence frequency. To address this concern and establish a set of baseline vibroacoustic characteristics, a representative test panel was fabricated and a suite of tests were conducted that involved measurements of panel vibration and radiated sound power during point force and diffuse acoustic field excitations. Experimental results are shown and compared with Finite Element and Statistical Energy Analysis model predictions through the use of modal and energy correlation techniques among others. The behavior of the structure subject to turbulent boundary layer excitation is also numerically examined.