A Truncated Low Approach of Intrinsic Linear and Nonlinear Damping in Thin Structures

[+] Author and Article Information
Yves Gourinat1

Department of Mechanics, Structures, and Materials, SUPAERO, Toulouse, Franceyves.gourinat@supaero.fr

Victorien Belloeil

Department of Mechanics, Structures, and Materials, SUPAERO, Toulouse, France and Department of Mechanical Engineering, ENSICA, Toulouse, France


Corresponding author.

J. Vib. Acoust 129(1), 32-38 (Apr 25, 2006) (7 pages) doi:10.1115/1.2358153 History: Received November 25, 2005; Revised April 25, 2006

An adaptive approach of vibrating thin structures is proposed here. The method consists in applying an equivalent adimensional damping ratio to each potential resonance. This ratio is deduced from experimental data obtained in vacuum facility, in relation with frequencies, for several structural technologies. Consequently, it is possible to calculate the structure in a linear nondissipative context, valid out of resonance bands, and truncated in those bands. Thus, the equivalent damping ratio is directly used to define adimensional resonance truncation bandwith and level. The contribution consists in tested and applied modal methodology and algebraic representations of damping including several dissipations—viscous and internal microfrictions—inducing a nonmonotonous model. The here aim is to provide realistic recommendations for simple vibrational analysis of aerospace thin structures—panels and stiffeners.

Copyright © 2007 by American Society of Mechanical Engineers
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Figure 5

Explicit numerical integration of vibrating equations with friction

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Figure 6

On an aluminum plate under vacuum, the effect of temperature is shown, which has a certain influence mainly on the second mode (twisting), and which also adds noise on measurement

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Figure 7

Effective modal elementary systems and truncations

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Figure 8

Schematic process for structural discretization

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Figure 9

Vacuum facility and mechanical fixture in chamber (photo: ENSICA)

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Figure 10

Measured temporal free response of carbon plate—analogy with mixed system

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Figure 11

Measured frequential excited response of carbon plate compared with viscosity

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Figure 12

Measured damping in composite bolted plate—proposed analytic curve

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Figure 13

Principle of truncations in amplitude with empirical intrinsic curve

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Figure 14

Influence of vacuum on fundamental modes in bending and twisting of a 2024-T4 aluminum plate dynamically excited. The effect of temperature is shown, with a certain influence mainly on the second mode (twisting) and addition of noise on measurement.

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Figure 1

Linear viscous and nonlinear friction free motion elementary solutions

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Figure 2

Excitation in force or in deflection, presented on linear conservative system

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Figure 3

Amplitude ratio logarithmic adimensional frequency graph and Cartesian zooming

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Figure 4

Amplitude ratio algorithmic adimensional frequency graph and Cartesian zooming




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