NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Aircraft Interior Noise Control Using Distributed Piezoelectric ActuatorsDeveloping a control system that can reduce the noise and structural vibration at the same time is an important task. This talk presents one possible technical approach for accomplishing this task. The target application of the research is for aircraft interior noise control. The emphasis of the present approach is not on control strategies, but rather on the design of actuators for the control system. In the talk, a theory of distributed piezoelectric actuators is introduced. A uniform cylindrical shell is taken as a simplified model of fuselage structures to illustrate the effectiveness of the design theory. The actuators developed are such that they can reduce the tonal structural vibration and interior noise in a wide range of frequencies. Extensive computer simulations have been done to study various aspects of the design theory. Experiments have also been conducted and the test results strongly support the theoretical development.
Document ID
19960047665
Document Type
Conference Paper
Authors
Sun, Jian Q. (Delaware Univ. Newark, DE United States)
Date Acquired
August 17, 2013
Publication Date
March 1, 1996
Publication Information
Publication: Proceedings of the 4th Annual Workshop: Advances in Smart Materials for Aerospace Applications
Subject Category
Acoustics
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

IDRelationTitle19960047656Analytic PrimaryProceedings of the 4th Annual Workshop: Advances in Smart Materials for Aerospace Applications
Document Inquiry