Apparatus and method for global noise reduction

• US 4,715,559 A
• Filed: 05/15/1986
• Issued: 12/29/1987
• Est. Priority Date: 05/15/1986
• Status: Expired due to Term

• Current Assignee: Verity Group PLC
• Original Assignee: Virginia Polytechnic Institute and State University
• Inventors: Fuller, Christopher R.
• Primary Examiner(s): Peters, Jr., Joseph F.
• Assistant Examiner(s): Corl, Rodney
• Application Number:
  US06/863,937
• Time in Patent Office: 593 Days
• Field of Search: 244/1 N, 244/75 A, 181/206, 381/71, 381/94
• US Class Current: 244/1.00N
• CPC Class Codes: A61F 11/145 electric, e.g. for active noise reduction
• CPC Class Codes: B64C 1/40 Sound or heat insulation , e.g. using insulation blankets
• CPC Class Codes: G10K 11/17823 Reference signals, e.g. ambient acoustic environment
• CPC Class Codes: G10K 11/17853 of the filter
• CPC Class Codes: G10K 11/17857 Geometric disposition, e.g. placement of microphones
• CPC Class Codes: G10K 11/17883 the reference signal being derived from a machine operating condition, e.g. engine RPM or vehicle speed
• CPC Class Codes: G10K 2210/3046 Multiple acoustic inputs, multiple acoustic outputs

Abstract

Apparatus is disclosed for attenuating sound radiated from a vibrating surface into a control volume as comprised of a source of a control signal indicative of the amplitude and frequency content of the sound transmitted from the vibrating surface. An actuator(s) or shaker is directly connected to the vibrating surface for further vibrating the vibrating surface to induce a cancelling sound into the control volume for combining with and attenuating the transmitted sound. A sensor(s) is also disposed within the control volume for detecting the resultant sound indicative of the combination of the cancelling and the transmitted sound to provide an error signal indicative thereof. A controller in the illustrative form of a computer executing a minimization algorithm, is responsive to the error signal for adaptively modifying the control signal as to phase and amplitude, which modified signal is applied to drive the actuator(s), whereby the error signal is driven to a minimum level and the sound within the control volume is similarly attenuated. One illustrative embodiment of this invention is particularly adapted to attenuate sound within the fuselage of an aircraft, wherein the principle source of noise is derived from the aircraft'"'"'s engine and propeller and is introduced through the aircraft'"'"'s fuselage into the aircraft'"'"'s cabin. The actuator is coupled directly to the fuselage and is energized with the control signal adaptively modified as to phase and amplitude such that the cancelling sound emanating from the actuator(s) combines with and attenuates the engine and propeller noise within the aircraft cabin.

Claims

1. Apparatus for attenuating sound radiated from a vibrating surface intoa control volume surrounded by the vibrating surface, said apparatus comprising:

(a) means for providing a control signal indicative of the frequency and amplitude of the sound radiated from said vibrating surface into said control volume;

(b) vibrating means directly connected to said vibrating surface for further vibrating said vibrating surface to induce a cancelling sound into said control volume for combining with an attenuating said radiated sound;

(c) detecting means disposed within said control volume for detecting the combination of said cancelling and said radiated sound to provide an error signal indicative thereof; and

(d) control means responsive to said error signal for adaptively modifying said control signal as to phase and amplitude and for applying said modified control signal to drive said vibrating means, whereby said error signal is driven to a minimum level.

2. The sound attenuating apparatus as claimed in claim 1, wherein there is "n" number of efficient coupling modes between said vibrating surface and said control volume, where "n" may equal 1, and said vibrating means includes "n" actuators coupled to said vibrating surface.

3. The sound attenuating apparatus as claimed in claim 1, wherein said detecting means comprises a plurality of sound sensors disposed in an array defining said control volume.

4. The sound attenuating apparatus as claimed in claim 1, wherein a sound source emanates sound in a sound plane intersecting said vibrating surfce to define an intersecting line therewith, said vibrating means directly coupled to said vibrating surface at a point spaced a distance sufficiently close to said intersecting line to effectively attenuate said radiated sound.

5. The sound attenuating apparatus as claimed in claim 1, wherein there is included a housing including said vibrating surface, said housing enclosing said control volume and including a dimension defining the extent of said control volume, and a sound source for emanating sound along a sound plane intersecting said housing to define an intersecting line therebetween, said vibrating means including at least one actuator directly coupled to said housing at a point spaced from said intersecting line a distance less than said dimension to effectively attenuate the sound radiated into said control volume.

6. The sound attenuating apparatus as claimed in claim 5, wherein said detecting means comprises a plurality of sound sensors disposed in an array within said housing to define the extent of said control volume.

7. The apparatus of claim 1, wherein said modified control signal drives said vibrating means to vibrate said vibrating surface at predetermined frequencies to induce a cancelling sound for combining with and attenuating only those sounds that radiate into said control volume.

8. Apparatus for attenuating sound within an aircraft fuselage emanating from an aircraft engine, said aircraft engine transmitting sound along a sound plane intersecting said aircraft fuselage to define a circumferential line intersecting therewith, said fuselage enclosing and surrounding a control volume, said sound attenuating apparatus comprising:

(a) means for providing a control signal indicative of the frequency and amplitude of the sound transmitted from aircraft engine through said vibrating fuselage and into said control volume;

(b) vibrating means directly connected to said aircraft fuselage for vibrating said aircraft fuselage to induce a cancelling sound into said control volume for combining with an attenuating said transmitted sound;

(c) means disposed within said control volume for detecting the combination of said cancelling sound and said transmitted sound to provide an error signal indicative thereof; and

(d) control means responsive to said error signal for adaptively modifying said control signal as to phase and amplitude and for applying said modified control signal to drive said vibrating means, whereby said error signal is driven to a minimal level and said transmitted sound within said control volume is minimized.

9. The aircraft sound attenuating apparatus as claimed in claim 8, wherein said detecting means comprises a plurality of sound sensors disposed within said fuselage for defining the extent of said control volume.

10. The aircraft sound attenuating apparatus as claimed in claim 8, wherein there is a limited number "n" of shell modes efficiently coupled between said fuselage and said control volume, where "n" may equal 1, and said vibrating means includes "n" number of actuators directly coupled to said fuselage.

11. The aircraft sound attenuating apparatus as claimed in claim 8, wherein there is a limited number "n" of shell modes efficiently coupled between said fuselage and said control volume, where "n" may equal 1, and said detecting means includes a plurality of "m" microphones, where "m" equals 2 "n" .

12. The aircraft sound attenuating apparatus as claimed in claim 8, wherein said fuselage has a cross-sectional diameter, and said vibrating means is directly coupled to said fuselage at a point spaced a distance not greater than said fuselage diameter from said intersecting line.

13. The aircraft sound attenuating apparatus as claimed in claim 8, wherein said sound sensing means comprises a sensor engaged on the outside of said fuselage with respect to said control volume for sensing the vibration induced by said aircraft engine in said fuselage for providing said control signal indicative thereof.

14. The aircraft sound attenuating apparatus as claimed in claim 8, said aircraft engine rotatably drives a propeller at a varying rotational velocity, said aircraft propeller defining a propeller plane along which the sound emanates therefrom into said fuselage defining a circumferential line intersecting therebetween, said sound sensing means responsive to the propeller noise for providing said control signal indicative thereof.

15. The aircraft sound attenuating apparatus as claimed in claim 14, wherein said sound sensing means is responsive to the rotational velocity of said aircraft propeller to provide said control signal indicative thereof.

16. The aircraft sound attenuating apparatus as claimed in claim 14, wherein said sound sensor provides said control signal of a fundamental frequency proportional to the velocity of said aircraft propeller and of the number of blades of said aircraft propeller.

17. The aircraft sound attenuating apparatus as claimed in claim 16, wherein said sound sensing means further includes means responsive to said control signal of said fundamental frequency for further generating and combining together "n" signals of higher harmonics of said fundamental frequency, where "n" may equal 1.

18. The aircraft sound attenuating apparatus as claimed in claim 8, wherein said control means comprises means for adjusting the phase and amplitude of said control signal for driving said vibrating means and a computer responsive to said error signal for executing a minimization program to control the phase and amplitude adjustment of said control signal.

19. The aircraft sound attenuating apparatus as claimed in claim 18, wherein said vibrating means comprises a plurality of "n" actuators coupled to said fuselage, said control means for dividing said control signal into "n" control signals and controlling the phase and amplitude of each of said "n" control signals.

20. The aircraft sound attenuating apparatus as claimed in claim 18, wherein said minimization program effects a Widrow-Hoff least mean square algorithm.

21. The apparatus of claim 8, wherein said aircraft engine exhibits a plurality of dominant frequencies, each of said frequencies causing at least one radiating shell mode within said vibrating surface, said shell mode being of the type radiating sound into said control volume, and said vibrating means operative to attenuate each of said radiating shell modes.

22. Apparatus for attenuating noise radiated from a vibrating surface as a radiated noise field at least partially surrounded by said vibrating surface, said apparatus comprising:

(a) means for providing a control signal indicative of the frequency and amplitude of the noise within said radiated noise field;

(a) vibrating means directly connected to said vibrating surface for further vibrating said vibrating surface to induce a cancelling sound into said radiating noise field for combining with and attenuating said radiated noise;

(c) a plurality of sensors disposed in an array defining a control volume within said radiation noise field, each sensor for detecting the combination of said cancelling sound and said radiated noise to provide an error singal indicative thereof; and

(d) control means responsive to said error signal for adaptively modifying said control signal as to phase and amplitude and for applying said modified control signal to drive said vibrating means, whereby said error signal is driven to a minimum level and said noise within said control volume is attenuated.

23. The noise attenuating apparatus as claimed in claim 22, wherein said array of sound sensors defines a perimeter of said control volume.

24. The noise attenuating apparatus as claimed in claim 22, wherein said noise comprises a standing wave of a maximum frequency and having a given spacing between a pair of adjacent nodes thereof, wherein adjacent sensors of said array are spaced from each other a distance substantially equal to said given spacing.