Experimental study of smart segmented trim panels for aircraft interior noise control

被引：17

作者：

Hirsch, SM ^{[1
]}

Meyer, NE ^{[1
]}

Westervelt, MA ^{[1
]}

King, P ^{[1
]}

Li, FJ ^{[1
]}

Petrova, MV ^{[1
]}

Sun, JQ ^{[1
]}

机构：

[1] Univ Delaware, Dept Mech Engn, Newark, DE 19716 USA

来源：

JOURNAL OF SOUND AND VIBRATION | 2000年 / 231卷 / 04期

基金：

美国国家科学基金会;

关键词：

D O I：

10.1006/jsvi.1999.2447

中图分类号：

O42 [声学];

学科分类号：

070206 ; 082403 ;

摘要：

A smart trim panel used as a secondary source for active noise control in aircraft is developed and tested. The smart trim panel is a rectangular segment of aircraft trim panel which is suspended by a flexible support. This support converts the stiff trim panel into flexibly mounted pistons which can be driven by light-weight and low-profile force actuators. The smart trim panel has many advantages as an acoustic source over traditional loudspeakers: it is of lower profile, lower mass, and requires only a simple modification of materials already installed on aircraft. The static and dynamic properties of a smart trim panel are studied, verifying that when subjected to low-frequency ( < 500 Hz) excitation, it vibrates in the efficiently radiating piston mode. Real-time active noise control experiments are conducted in a laboratory-scale fuselage model using the smart trim panels as secondary sources. Global attenuation of sound pressure levels of up to 15 dB is realized. (C) 2000 Academic Press.

引用

页码：1023 / 1037

页数：15

共 35 条

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