Apparatus and method for active control of sound transmission through aircraft fuselage walls

• US 6,078,673 A
• Filed: 10/03/1997
• Issued: 06/20/2000
• Est. Priority Date: 10/03/1997
• Status: Expired due to Term

• Current Assignee: Hood Technology Corporation
• Original Assignee: Hood Technology Corporation
• Inventors: Tappert, Peter M., von Flotow, Andreas H., Mercadal, Mathieu
• Primary Examiner(s): Lee, Ping
• Application Number:
  US08/943,403
• Time in Patent Office: 991 Days
• Field of Search: 381/71.7, 381/71.11, 381/71.14, 381/71.4, 381/71.1
• US Class Current: 381/71.7
• CPC Class Codes: B64C 1/40 Sound or heat insulation , e.g. using insulation blankets
• CPC Class Codes: G10K 11/17857 Geometric disposition, e.g. placement of microphones
• CPC Class Codes: G10K 11/17875 using an error signal without a reference signal, e.g. pure feedback

Abstract

In aircraft, much of the noise in the cabin is a result of pressure fluctuations on the exterior fuselage skin, which vibrates the skin and causes sound pressure waves to propagate through the trim panel cavity, exciting the trim panels, which radiate into the cabin. In the present invention, noise is reduced in the cabin of an aircraft by reducing the acoustical impedance of the trim panel cavity of the aircraft using an array of independent active sound absorbing acoustic cells. Acoustical drivers are mounted within the trim panel cavity of the aircraft. Each acoustical driver has at least one electroacoustical sensor mounted in its immediate vicinity. The sensor is connected to the driver to provide negative feedback, which has the effect of canceling noise in the vicinity of each cell. Since the effect of each cell is to absorb acoustical energy, the acoustical impedance of the trim panel cavity is reduced. Multiple sound absorbing acoustic cells in the trim panel cavity therefore decrease the acoustical impedance inside the trim panel cavity which in turn reduces the transmission of noise into the cabin.

Claims

1. A system for attenuating noise in a cabin of an aircraft, the aircraft having an interior wall defining the cabin, and an exterior fuselage defining a trim panel cavity between the fuselage and the interior wall, the system comprising a plurality of acoustically active cells mounted in the trim panel cavity, and an electroacoustical sensor and an acoustical driver mounted within each cell, wherein a distance between the sensor and the driver is less than a distance between adjacent cells, and wherein the sensor transduces sound pressure in the cavity to produce an electrical signal which is inversely fed back to the driver to reduce sound pressure around the cell without a reference microphone.

2. The system of claim 1, wherein

the acoustical driver has an input for receiving the electrical signal and a vibratable diaphragm providing an acoustic output signal according to the input;

wherein each acoustically active cell further comprises a housing supporting the acoustical driver and making the acoustical driver a source of acoustic volume;

an amplifier having an input for receiving the transduced electrical signal and an output for providing an amplified signal to the input of the acoustical driver in an inverse feedback connection,

whereby the cell produces in the cavity a signal component tending to cancel the acoustical pressure signal in the cavity.

3. The system of claim 2, wherein a distance between the acoustical driver and the electroacoustical sensor is less than a distance between the plurality of acoustically active cells.

4. The system of claim 2, wherein the inverse feedback connection comprises:

a compensation circuit establishing an open loop gain having a maximum gain over a redetermined range of frequencies.

5. A system for attenuating noise in a cabin of an aircraft, the aircraft having an interior wall defining the cabin, and an exterior fuselage defining a trim panel cavity between the fuselage and the interior wall, the system comprising a plurality of acoustically active cells mounted in the trim panel cavity, wherein each acoustically active cell comprises:

means for transducing sound pressure in the vicinity of a driver of a sound pressure source in the cavity to provide an electrical signal; and

means for inversely feeding back the electrical signal to the driver without a reference microphone;

wherein a distance between the means for transducing sound pressure and the driver is less than a distance between the adjacent acoustically active cells, and wherein each acoustically active cell reduces sound pressure around the cell.

6. A process for attenuating noise in a cabin of an aircraft, the aircraft having an interior wall defining the cabin, and an exterior fuselage defining a trim panel cavity between the fuselage and the interior wall, a plurality of acoustically active cells in the cavity, each cell having an electroacoustical sensor and an acoustical driver, a distance between the sensor and the driver being less than a distance between the adjacent cells, the process comprising the steps of:

for each of the cells transducing sound pressure with the sensor in the vicinity of the driver to provide an electrical signal; and

for each of the cells inversely feeding back the electrical signal to the driver without a reference microphone.