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Identification of structural parameters from helicopter dynamic test dataA method is presented for obtaining the mass, stiffness, and damping parameters of a linear mathematical model, having fewer degrees of freedom than the structure it represents, directly from dynamic response measurements on the actual helicopter without a priori knowledge of the physical characteristics of the fuselage. The only input information required in the formulation is the approximate natural frequency of each mode and mobility data measured proximate to these frequencies with sinusoidal force excitation applied at only one point on the vehicle. The practicality and numerical soundness of the theoretical development was demonstrated through a computer simulation of an experimental program.
Document ID
19740026400
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Giansante, N. (Kaman Aircraft Corp. Bloomfield, CT, United States)
Flannelly, W. G. (Kaman Aircraft Corp. Bloomfield, CT, United States)
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
74N34513
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle19740026376Collected WorksRotorcraft dynamics
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