A principal component feedforward algorithm for active noise control: flight test results

An in-flight evaluation of a principal component algorithm for feedforward active noise control is discussed. Cabin noise at the first three harmonics of the blade passage frequency (103 Hz) of a Raytheon-Beech 1900D twin turboprop aircraft was controlled using 21 pairs of inertial force actuators bolted to the ring frames of the aircraft; 32 microphones provided error feedback inside the aircraft cabin. In a single frequency noise control test, the blade passage frequency was reduced by 15 dB averaged across the microphone array. When controlling the first three harmonics simultaneously, reductions of 11 dB at 103 Hz, 1.5 dB at 206 Hz, and 2.8 dB at 309 Hz were obtained. For single frequency feedforward control problems, the principal component algorithm is shown to be useful for reducing the computational burden and simplifying the implementation of control effort penalties in high channel count control systems. Good agreement was found between the in-flight behavior of the controller and the predicted optimal control solution.

[1]  D. Photiadis,et al.  The structural acoustics and active control of interior noise in a ribbed cylindrical shell , 1996 .

[2]  B. Moore.  Principal component analysis in linear systems: Controllability, observability, and model reduction , 1981 .

[3]  C. Fuller,et al.  Mechanisms of active control in cylindrical fuselage structures , 1987 .

[4]  Simon Haykin,et al.  Adaptive filter theory (2nd ed.) , 1991 .

[5]  G. P. Eatwell,et al.  A demonstration of active noise reduction in an aircraft cabin , 1989 .

[6]  Richard J. Silcox,et al.  Evaluation of piezoceramic actuators for control of aircraft interior noise , 1992 .

[7]  Philip A. Nelson,et al.  Models for evaluating the performance of propeller aircraft active noise control systems , 1987 .

[8]  Philip A. Nelson,et al.  Active Control of Sound , 1992 .

[9]  I. Stothers,et al.  In-flight experiments on the active control of propeller-induced cabin noise , 1990 .

[10]  R. J. Silcox,et al.  Active control of interior noise in a large scale cylinder using piezoelectric actuators , 1992 .

[11]  Chris R. Fuller,et al.  Active control of propeller-induced noise fields inside a flexible cylinder , 1990 .

[12]  Palumbo Dan,et al.  Flight Test of ASAC Aircraft Interior Noise Control System , 1999 .

[13]  Chris R. Fuller,et al.  A PRINCIPAL COMPONENT ALGORITHM FOR FEEDFORWARD ACTIVE NOISE AND VIBRATION CONTROL , 1999 .

[14]  Richard J. Silcox,et al.  Mechanisms of active control in cylindrical fuselage structures , 1987 .

[15]  Philip A. Nelson,et al.  The active minimization of harmonic enclosed sound fields, part I: Theory , 1987 .

[16]  L. J. Eriksson,et al.  Use of random noise for on‐line transducer modeling in an adaptive active attenuation system , 1986 .

[17]  C. Fuller,et al.  Experiments on reduction of propeller induced interior noise by active control of cylinder vibration , 1987 .

[18]  Stephen J. Elliott,et al.  A multiple error LMS algorithm and its application to the active control of sound and vibration , 1987, IEEE Trans. Acoust. Speech Signal Process..

[19]  Steve C. Southward,et al.  Control effort weighting in feedforward adaptive control systems , 1996 .

[20]  Stephen J. Elliott,et al.  Active Control of the Transmission of Sound Through a Thin Cylindrical Shell, Part I: the Minimization of Vibrational Energy , 1993 .