NDLI: Radiated sound power from a curved honeycomb panel

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Radiated sound power from a curved honeycomb panel

Content Provider	NASA Technical Reports Server (NTRS)
Author	Robinson, Jay H. Grosveld, Ferdinand W. Buehrle, Ralph D. Klos, Jacob
Copyright Year	2003
Description	The validation of finite element and boundary element model for the vibro-acoustic response of a curved honeycomb core composite aircraft panel is completed. The finite element and boundary element models were previously validated separately. This validation process was hampered significantly by the method in which the panel was installed in the test facility. The fixture used was made primarily of fiberboard and the panel was held in a groove in the fiberboard by a compression fitting made of plastic tubing. The validated model is intended to be used to evaluate noise reduction concepts from both an experimental and analytic basis simultaneously. An initial parametric study of the influence of core thickness on the radiated sound power from this panel, using this numerical model was subsequently conducted. This study was significantly influenced by the presence of strong boundary condition effects but indicated that the radiated sound power from this panel was insensitive to core thickness primarily due to the offsetting effects of added mass and added stiffness in the frequency range investigated.
File Size	1153263
Page Count	8
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_20030069018
Archival Resource Key	ark:/13960/t58d4vt0d
Language	English
Publisher Date	2003-01-01
Access Restriction	Open
Subject Keyword	Aircraft Design, Testing And Performance Damping Finite Element Method Noise Reduction Stiffness Frequencies Honeycomb Structures Aircraft Structures Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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