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Local feedback control of light honeycomb panels

Local feedback control of light honeycomb panels
Local feedback control of light honeycomb panels
This paper summarizes theoretical and experimental work on the feedback control of sound radiation from honeycomb panels using piezoceramic actuators. It is motivated by the problem of sound transmission in aircraft, specifically the active control of trim panels. Trim panels are generally honeycomb structures designed to meet the design requirement of low weight and high stiffness. They are resiliently mounted to the fuselage for the passive reduction of noise transmission. Local coupling of the closely spaced sensor and actuator was observed experimentally and modeled using a single degree of freedom system. The effect of the local coupling was to roll off the response between the actuator and sensor at high frequencies, so that a feedback control system can have high gain margins. Unfortunately, only relatively poor global performance is then achieved because of localization of reduction around the actuator. This localization prompts the investigation of a multichannel active control system. Globalized reduction was predicted using a model of 12-channel direct velocity feedback control. The multichannel system, however, does not appear to yield a significant improvement in the performance because of decreased gain margin
0001-4966
222-233
Hong, Chinsuk
f739363c-b9f4-47b6-9398-178f965f403e
Elliott, Stephen J.
721dc55c-8c3e-4895-b9c4-82f62abd3567
Hong, Chinsuk
f739363c-b9f4-47b6-9398-178f965f403e
Elliott, Stephen J.
721dc55c-8c3e-4895-b9c4-82f62abd3567

Hong, Chinsuk and Elliott, Stephen J. (2007) Local feedback control of light honeycomb panels. Journal of the Acoustical Society of America, 121 (1), 222-233. (doi:10.1121/1.2384843).

Record type: Article

Abstract

This paper summarizes theoretical and experimental work on the feedback control of sound radiation from honeycomb panels using piezoceramic actuators. It is motivated by the problem of sound transmission in aircraft, specifically the active control of trim panels. Trim panels are generally honeycomb structures designed to meet the design requirement of low weight and high stiffness. They are resiliently mounted to the fuselage for the passive reduction of noise transmission. Local coupling of the closely spaced sensor and actuator was observed experimentally and modeled using a single degree of freedom system. The effect of the local coupling was to roll off the response between the actuator and sensor at high frequencies, so that a feedback control system can have high gain margins. Unfortunately, only relatively poor global performance is then achieved because of localization of reduction around the actuator. This localization prompts the investigation of a multichannel active control system. Globalized reduction was predicted using a model of 12-channel direct velocity feedback control. The multichannel system, however, does not appear to yield a significant improvement in the performance because of decreased gain margin

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Published date: 2007

Identifiers

Local EPrints ID: 45648
URI: http://eprints.soton.ac.uk/id/eprint/45648
ISSN: 0001-4966
PURE UUID: c8f4886d-02c0-492c-9ad9-688252f7e643

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Date deposited: 16 Apr 2007
Last modified: 15 Mar 2024 09:12

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Author: Chinsuk Hong

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