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Correlation of finite-element structural dynamic analysis with measured free vibration characteristics for a full-scale helicopter fuselageThe correlation achieved with each program provides the material for a discussion of modeling techniques developed for general application to finite-element dynamic analyses of helicopter airframes. Included are the selection of static and dynamic degrees of freedom, cockpit structural modeling, and the extent of flexible-frame modeling in the transmission support region and in the vicinity of large cut-outs. The sensitivity of predicted results to these modeling assumptions are discussed. Both the Sikorsky Finite-Element Airframe Vibration analysis Program (FRAN/Vibration Analysis) and the NASA Structural Analysis Program (NASTRAN) have been correlated with data taken in full-scale vibration tests of a modified CH-53A helicopter.
Document ID
19740026383
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kenigsberg, I. J.
(United Aircraft Corp. Stratford, CT, United States)
Dean, M. W.
(United Aircraft Corp. Stratford, CT, United States)
Malatino, R.
(Naval Air Systems Command)
Date Acquired
August 7, 2013
Publication Date
January 1, 1974
Publication Information
Publication: NASA. Ames Res. Center Rotorcraft Dyn.
Subject Category
Structural Mechanics
Accession Number
74N34496
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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