Broadband noise and vibration reduction

• US 5,526,292 A
• Filed: 11/30/1994
• Issued: 06/11/1996
• Est. Priority Date: 11/30/1994
• Status: Expired due to Fees

• Current Assignee: Lord Corporation (Parker-Hannifin Corporation)
• Original Assignee: Lord Corporation (Parker-Hannifin Corporation)
• Inventors: Hodgson, Douglas A., Jolly, Mark R., Southward, Steve C., Norris, Mark A., Swanson, Douglas A., Rossetti, Dino J.
• Primary Examiner(s): Teska, Kevin J.
• Assistant Examiner(s): FREJD, RUSSELL WARREN
• Application Number:
  US08/347,523
• Time in Patent Office: 559 Days
• Field of Search: 73/35, 381/71, 364/506, 364/439, 364/574, 267/140.11, 244/17.27, 244/1 N, 244/54
• US Class Current: 700/280
• 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 11/17854 the filter being an adaptive filter
• CPC Class Codes: G10K 11/17857 Geometric disposition, e.g. placement of microphones
• CPC Class Codes: G10K 11/17881 the reference signal being an acoustic signal, e.g. recorded with a microphone
• CPC Class Codes: G10K 2210/10 Applications
• CPC Class Codes: G10K 2210/103 Three dimensional
• CPC Class Codes: G10K 2210/124 Traffic
• CPC Class Codes: G10K 2210/3046 Multiple acoustic inputs, multiple acoustic outputs
• CPC Class Codes: G10K 2210/3217 Collocated sensor and cancelling actuator, e.g. "virtual earth" designs
• CPC Class Codes: G10K 2210/512 Wide band, e.g. non-recurring signals

Abstract

An active noise and vibration cancellation system with broadband control capability. A broadband disturbance signal detector positioned within a closed compartment such as an aircraft cabin or vehicle passenger compartment provides a signal representative of the frequency spectrum and corresponding relative magnitude of a broadband signal emanating from a vibrational energy source to a controller. The controller receives the broadband disturbance signal as well as error signals from error sensors which, by virtue of adaptive filters within the controller, enhance the cancellation capability of the control signals produced by one or more actuators positioned within the compartment.

Claims

1. A system for canceling vibrational energy within a passenger compartment comprising:

a) reference signal detecting means for sensing a frequency spectrum and corresponding relative magnitude of a broadband signal emanating from at least one vibrational energy source to which said compartment is exposed, said broadband signal including sound energy, said detecting means being situated in a key location with respect to said energy source to intercept said broadband signal on its way to said compartment;

b) error sensor means for detecting a residual internal level of vibrational energy within said compartment, said error sensor means being positioned down stream of said reference sensor detecting means;

c) actuator means placed to provide a control signal of appropriate frequency and magnitude to cancel some portion of said broadband vibrational signal, said actuator means including;

i) first actuator means producing a control signal spanning a first frequency range, and

ii) second actuator means producing a control signal spanning a second frequency range different from said first frequency range;

d) an adaptive controller including adaptive filters for generating broadband, time-domain command signals to activate said actuator means responsive to

i) said detecting means, and

ii) said error sensor means

to generate control signals of appropriate frequency and magnitude to destructively interfere with said broadband vibrational signal.

2. The system for canceling noise and vibration of claim 1 wherein said actuator means comprises one or more speakers positioned within said compartment.

3. The system for canceling noise and vibration of claim 2 wherein said actuator means further comprises a series of actuators attached to portions of a structure forming said compartment which can be activated to vibrate said structure at a rate to cancel some portion of said broad-band signal.

4. An active vibration control system for controlling broadband vibrational energy within a passenger compartment of an aircraft or the like, comprising:

a) reference sensor means for monitoring a broadband vibrational energy input signal to be controlled, said reference sensor means being positioned within said passenger compartment proximate a point of entry for said broadband vibrational energy input signal, said vibrational energy input signal having various spectral frequencies, said sensor means producing a reference signal which corresponds to said broadband vibrational energy input signal;

b) first actuator means for producing a first control signal for destructively interfering with at least a first portion of said broadband vibrational energy input signal, said first control signal spanning a first range of frequencies;

c) second actuator means for producing a second control signal for destructively interfering with at least a second portion of said broadband vibrational energy input signal, said second control signal spanning a second range of frequencies at least some of which are different from said first range of frequencies;

d) an adaptive controller including adaptive filter means for processing said reference signal and producing at least two actuator command signals, one each to said first and second actuator means, which are of appropriate frequency and magnitude to activate a respective said actuator means;

e) error sensor means for sensing a residual signal resulting from combining said first and second control signals with said input signal, and

f) circuitry means for feeding said residual signal back to said adaptive filter means to make adjustments in said actuator command signals.

5. The active vibrational control system of claim 4 wherein said aircraft comprises a turboprop.

6. The active vibrational control system of claim 5 wherein said reference sensor means is located on a wing spar adjacent a fusilage portion subject to prop wash of a turboprop power plant.

7. The active vibrational control system of claim 4 wherein said aircraft comprises a turbofan.

8. The active vibration control system of claim 7 wherein said reference sensor means comprise one or more spaced microphones within said enclosure.

9. The active vibration control system of claim 8 wherein said error sensor means comprise one or more spaced accelerometers attached to structural portions of said enclosure.

10. The active vibration control system of claim 9 wherein said enclosure comprises an aircraft cabin and said input signal includes external air noise created by vortices in a boundary layer flowing about an external portion of said aircraft'"'"'s fusilage.

11. The active vibration control system of claim 4 wherein said circuitry means produces said actuator command signals in accordance with a weighted sum of said signals from said reference signal sensor means and said error sensor means.

12. An active vibration control system for controlling vibrational energy within a passenger compartment of an aircraft employing first and second active mounts for supporting respectively its first and second power plants comprising

a) first reference sensor means for monitoring a vibrational energy input signal to be controlled including at least one accelerometer mounted on said first power plant, said sensor means producing a first reference signal which corresponds to at least a portion of said vibrational energy input signal;

b) second reference sensor means for monitoring a vibrational energy input signal to be controlled including at least one accelerometer mounted on said second power plant, said sensor means producing a second reference signal which corresponds to at least a portion of said vibrational energy input signal;

c) first actuator means contained with said active mount for producing a first control signal reducing at least a first portion of said vibrational energy input signal by countering motion resulting from said first power plant;

d) second actuator means contained within said active mount for producing a second control signal reducing at least a second portion of said vibrational energy input signal by countering motion resulting from said second power plant;

e) an adaptive controller including adaptive filter means for processing said first and second reference signals and producing at least two actuator command signals, one each to said first and second actuator means, which are of appropriate frequency and magnitude to activate a respective said actuator means;

f) error sensor means for sensing a residual signal resulting from combining said first and second control signals with said vibrational energy input signal, and

g) circuitry means for feeding said residual signal back to said adaptive filter means to make adjustments in said actuator command signals.

13. The active vibration control system of claim 12 wherein said circuitry means produces said actuator command signals in accordance with a weighted sum of said signals from said reference signal sensor means and said error sensor means.

14. The active vibrational control system of claim 12 wherein said first and second actuator means each comprise a plurality of structural actuators positioned within said first and second active mounts.