# US 5,568,557 A · Active vibration control system for aircraft

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- Number: US 5,568,557 A
- Document ID: US5568557A
- Status: Granted
- Kind: A
- Application number: 08/283,114
- Filed: 1994-07-29
- Granted: 1996-10-22
- Earliest claimed: 1994-07-29
- Assignees: Noise Cancellation Technologies, Inc.
- Inventors: Colin F. Ross; Andrew J. Langley
- Web page: https://patentgrep.com/patent/US5568557A

## CPC

- G10K 11/17825: {Error signals}
- G10K 11/17835: {using detection of abnormal input signals}
- G10K 11/17857: {Geometric disposition, e.g. placement of microphones}
- G10K 11/17883: {the reference signal being derived from a machine operating condition, e.g. engine RPM or vehicle speed}
- G10K 2210/1053: Hi-fi, i.e. anything involving music, radios or loudspeakers
- G10K 2210/106: Boxes, i.e. active box covering a noise source; Enclosures
- G10K 2210/1082: Microphones, e.g. systems using "virtual" microphones
- G10K 2210/12: Rooms, e.g. ANC inside a room, office, concert hall or automobile cabin
- G10K 2210/123: Synchrophasors or other applications where multiple noise sources are driven with a particular phase relationship
- G10K 2210/128: Vehicles
- G10K 2210/1281: Aircraft, e.g. spacecraft, airplane or helicopter
- G10K 2210/1282: Automobiles
- G10K 2210/30232: Transfer functions, e.g. impulse response
- G10K 2210/3031: Hardware, e.g. architecture
- G10K 2210/3051: Sampling, e.g. variable rate, synchronous, decimated or interpolated
- G10K 2210/321: Physical
- G10K 2210/3212: Actuator details, e.g. composition or microstructure
- G10K 2210/3214: Architectures, e.g. special constructional features or arrangements of features
- G10K 2210/3221: Headrests, seats or the like, for personal ANC systems
- G10K 2210/503: Diagnostics; Stability; Alarms; Failsafe
- G10K 2210/511: Narrow band, e.g. implementations for single frequency cancellation
- G10K: SOUND-PRODUCING DEVICES; METHODS OR DEVICES FOR PROTECTING AGAINST, OR FOR DAMPING, NOISE OR OTHER ACOUSTIC WAVES IN GENERAL; ACOUSTICS NOT OTHERWISE PROVIDED FOR

## Abstract

An active noise and vibration reduction system for canceling noise in aircraft or other passenger carrying transportation systems which utilizes a series of seat mounted microphones and trim mounted speakers in conjunction with a digital controller with a class-D stage power amplifier and which is synched to the aircraft alternator.

## Claims

### Claim 1

An active control system for reducing the tonal vibration in the cabin of an aircraft, helicopter or other passenger carrying cabin comprising:
individual power amplifier means,
actuator means combined with said individual power amplifier means and adapted to produce an additional vibration field,
trim-mounted sensing means adapted to generate signals responsive to sound in the cabin and insensitive to sound between the trim and the outer skin of the vehicle, and
a controller means responsive to the said sensing means signals and adapted to adjust signals to the said actuator means so that the said additional vibration field tends to reduce the said cabin vibration,
said controller means characterized in that it receives its speed reference signal from a power alternator on said vehicle and that the said power amplifier means contains an efficient class-D stage and wherein the said controller means monitors its own performance and switches off when the said monitored performance falls below a prescribed level and wherein it detects failures of the said sensing means and said actuator means.

### Claim 2 (depends on 1)

An active control system as claimed in claim 1 with at least a portion of said actuator means being loudspeakers, said loudspeakers contained in cabinets attached to said trim of said aircraft, helicopter or passenger cabin, and said cabinets being contoured to fit into the confined space between said trim and the outer skin, said cabinets containing stiffening webs, and said loudspeakers having coils with a long-throw and magnets containing rare-earth elements.

### Claim 3 (depends on 1)

An active control system as claimed in claim 1 with at least a portion of said actuator means being shakers, said shakers being of the inertial type with no external moving parts.

### Claim 4 (depends on 1)

An active control system as claimed in claim 1 with at least a portion of said actuator means being loudspeakers, said loudspeakers contained in cabinets attached to said trim of said aircraft or helicopter, and said cabinets being contoured to fit into the confined space between said trim and the fuselage, said cabinets containing stiffening webs, and said loudspeakers having coils with a long-throw and magnets containing rare-earth elements, and with shakers as at least some of the said actuators, said shakers being of the inertial type with no external moving parts.

### Claim 5 (depends on 1)

An active control system as claimed in claim 1 where at least a portion of the said actuator means are loudspeakers, said loudspeakers contained in cabinets attached to the trim of said aircraft or helicopter, and said cabinets being contoured to fit into the confined space between said trim and the fuselage, and said cabinets containing stiffening webs, said loudspeakers having coils with a long-throw and magnets containing rare-earth elements, and with shakers as at least some of the said actuators, said shakers being of the inertial type with no external moving parts.

### Claim 6 (depends on 1)

An active control system as claimed in claim 1 and including second sensing means mounted in the upper part of the backs of the cabin passenger seats, these said second sensing means being used to provide additional signals to said controller means responsive to the internal cabin sound.

### Claim 7 (depends on 1)

An active control system as claimed in claim 1 wherein said controller means is built in a modular form where the additional channels can be added by adding additional electronic circuit boards.

### Claim 8 (depends on 1)

An active control system as claimed in claim 1 and having additional controller means which are used for separate blocks of passenger seats.

### Claim 9 (depends on 1)

An active control system as claimed in claim 1 wherein said controller means operates on a constant sampling rate.

### Claim 10 (depends on 9)

An active control system as claimed in claim 9 wherein said controller means identifies the transfer function from the said actuator signals to the said sensing means signals at least part of the time that it is reducing said vibration field.

### Claim 11 (depends on 9)

An active control system as claimed in claim 9 wherein the system provides a signal to a synchrophase system for setting the relative angle of the propeller or engine shafts which is used to modify further said vibration field.

### Claim 12 (depends on 1)

An active control system as claimed in claim 1 wherein said controller means has a digital link or PWM link from it to said individual power amplifier means.

### Claim 13 (depends on 1)

An active control system as claimed in claim 1 wherein said actuator means are loudspeakers having drive units and being cabinets and in which the loudspeaker drive unit and the loudspeaker cabinet volume are tuned to provide the highest efficiency of output within the constraints imposed by a power amplifier and said loudspeaker drive unit motor.