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  • Other Sources  (2)
  • Aircraft Design, Testing and Performance  (2)
  • Spacecraft Design, Testing and Performance
  • 2000-2004  (2)
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  • Other Sources  (2)
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  • 1
    facet.materialart.
    Unknown
    Radiated Sound Power from a Curved Honeycomb Panel (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    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.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA Paper 2003-3156 , 9th AIAA/CEAS Aeroacoustics Conference and Exhibition; May 12, 2003 - May 14, 2003; Hilton Head, SC; United States
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 2
    facet.materialart.
    Unknown
    Sound Transmission Through a Curved Honeycomb Composite Panel (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Composite structures are often used in aircraft because of the advantages offered by a high strength to weight ratio. However, the acoustical properties of these light and stiff structures can often be less than desirable resulting in high aircraft interior noise levels. In this paper, measurements and predictions of the transmission loss of a curved honeycomb composite panel are presented. The transmission loss predictions are validated by comparisons to measurements. An assessment of the behavior of the panel is made from the dispersion characteristics of transverse waves propagating in the panel. The speed of transverse waves propagating in the panel is found to be sonic or supersonic over the frequency range from 100 to 5000 Hz. The acoustical benefit of reducing the wave speed for transverse vibration is demonstrated.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA Paper 2003-3157 , 9th AIAA/CEAS Aeroacoustics Conference and Exhibition; May 12, 2003 - May 14, 2003; Hilton Head, SC; United States
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
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