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Experimental test of semi-active shunt damping on a helicopter trim panel

Pohl, Martin and Haase, Thomas (2016) Experimental test of semi-active shunt damping on a helicopter trim panel. In: Proceedings of the European Rotorcraft Forum. 42. European Rotorcraft Forum, 06.-08. Sept. 2016, Lille, Frankreich.

Full text not available from this repository.

Abstract

The increased need for lightweight structures in modern aerospace transport due to lower fuel consumption and increased transport capacity reveals an acoustic challenge. Because of the high stiffness and low mass the coincidence frequencies of lightweight structures are low compared to classical aluminum structures. That is the reason for a weak transmission loss of lightweight structures made of glass or carbon fiber reinforced plastics. Therefore, passive solutions are widely investigated to increase the transmission loss of lightweight helicopter trim panels. For example, in the European GARTEUR AG 20 "Cabin internal noise: simulation and experimental methods for new solutions for internal noise reduction", two helicopter trim panels are studied which are structurally optimized for an increased TL. In this paper the applicability of a semi-active shunt damping system to this structurally optimized helicopter trim panel is investigated experimentally. Prior to this, the semi-active shunt damping performance is studied on a classical steel plate and afterwards the damped helicopter trim panel is investigated in a transmission loss facility. Two experiments are conducted. First of all, the trim panel is excited with a point force and the surface vibrations are measured with a laser scanning vibrometer. In the second test the trim panel is excited with a diffuse sound field. It can be seen that the negative capacitance shunt is less effective on a higher damped structure. Global vibration reductions of only $3-4\usk\deci\bel$ are achieved during the shaker test. Concerning the transmission loss, the results are comparable to the vibration reduction. The main reason for this is supposed to be a lower piezoelectric coupling to the sandwich panel.

Item URL in elib:https://elib.dlr.de/106013/
Document Type:Conference or Workshop Item (Speech)
Title:Experimental test of semi-active shunt damping on a helicopter trim panel
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Pohl, MartinMartin.Pohl (at) dlr.deUNSPECIFIED
Haase, ThomasThomas.Haase (at) dlr.dehttps://orcid.org/0000-0002-9553-9628
Date:2016
Journal or Publication Title:Proceedings of the European Rotorcraft Forum
Refereed publication:No
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Status:Published
Keywords:negative capacitance, piezoelectric shunt damping, helicopter, interior noise, trim panel
Event Title:42. European Rotorcraft Forum
Event Location:Lille, Frankreich
Event Type:international Conference
Event Dates:06.-08. Sept. 2016
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:rotorcraft
DLR - Research area:Aeronautics
DLR - Program:L RR - Rotorcraft Research
DLR - Research theme (Project):L - The Quiet und Comfortable Rotorcraft
Location: Braunschweig
Institutes and Institutions:Institute of Composite Structures and Adaptive Systems > Adaptronics
Deposited By: Pohl, Martin
Deposited On:12 Sep 2016 07:22
Last Modified:12 Sep 2016 07:22

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