Helicopter active noise control system

• US 5,310,137 A
• Filed: 04/16/1992
• Issued: 05/10/1994
• Est. Priority Date: 04/16/1992
• Status: Expired due to Term

• Current Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Welsh, William A., Yoerkie, Charles A. Jr., Sheehy, Thomas W.
• Primary Examiner(s): Focarino, Margaret A.
• Assistant Examiner(s): Ellis, Christopher P.
• Application Number:
  US07/870,434
• Time in Patent Office: 754 Days
• Field of Search: 244/17.27, 244/1 N, 244/17.11, 188/378, 188/379, 188/380, 74/606 R, 74/572, 74/574, 248/554-559
• US Class Current: 244/17.27
• CPC Class Codes: B64C 2220/00 Active noise reduction systems
• CPC Class Codes: B64C 27/001 Vibration damping devices
• CPC Class Codes: F16F 15/00 Suppression of vibrations in systems damping of non-rotary systems using inertia effect F16F7/10; prevention or isolation of vibrations in machine tools B23Q11/0032; suppression of driveline vibrations in hybrid vehicle transmissions B60W30/20 ; vehicle seat suspension devices B60N2/50; methods or devices for protecting against, or damping of, acoustic waves, e.g. sound G10K11/16; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion vibration absorbing or balancing means for aircraft propellers B64C11/008, for rotorcraft rotors B64C27/001 ; testing static and dynamic balance of machines or structures G01M1/00
• CPC Class Codes: Y10T 74/2186 Gear casings

Abstract

An active noise control (ANC) system for a helicopter that is operative to effectively nullify one or more high frequency vibrations emanating from the main transmission gearbox thereof at the gearbox/airframe interface, thereby significantly reducing the interior noise levels of the helicopter, that is design optimized to minimize the number of actuators required, and that is design optimized to minimize contamination forces arising from operation of the system actuators. The ANC system includes modified transmission beams that are mechanically stiffened to function as rigid bodies with respect to the one or more of the high frequency vibrations, a plurality of actuators disposed in combination with the modified transmission beams, a plurality of sensors disposed in combination with the modified transmission beams in a collinear, spaced apart functional correlation with respective actuators, and controllers interconnecting individual actuators with respective functionally correlated sensors.

Claims

1. An active noise control system for a helicopter for effectively nullifying high frequency vibrations emanating from the main transmission gearbox thereof to significantly reduce interior noise levels of the helicopter, comprising:

modified transmission beam means including mounting hardpoints for interfacing the main transmission gearbox in combination with the airframe of the helicopter, said modified transmission beam means being mechanically stiffened with respect to at least one of the high frequency vibrations emanating from the main transmission gearbox wherein said modified transmission beam means function as a rigid body with respect to said at least one high frequency vibration;

actuator means mounted in combination with said modified transmission beam means adjacent said transmission gearbox and airframe interface for generating a plurality of single dimensional counterforces having a frequency, magnitude, and phase to effectively nullify said at least one high frequency vibration at said transmission gearbox and airframe interface; and

means operative with respect to said at least one high frequency vibration to detect magnitudes and frequencies of single dimensional components thereof at said transmission gearbox and airframe interface and to provide command signals to control operation of said actuator means to generate said single dimensional counterforces having said frequency, magnitude, and phase to effectively nullify said at least one high frequency vibration at said transmission gearbox and airframe interface wherein the interior noise levels of the helicopter are significantly reduced.

2. The active noise control system of claim 1 wherein said detecting and providing means further comprises:

sensor means mounted in combination with said modified transmission beam means adjacent said transmission gearbox and airframe interface for detecting the magnitudes and frequencies of the single dimensional components of said at least one high frequency vibration and for generating detection signals representative thereof, and wherein said sensor means is mounted in combination with said transmission beams in collinear, spaced apart functional correlation with said respective actuators means; and

controller means functionally interconnecting said actuator means and said sensor means and operative in response to said detection signals for providing said command signals to control operation of said actuator means to generate said single dimensional counterforces having said frequency, magnitude, and phase to effectively nullify said at least one high frequency vibration at said transmission gearbox and airframe interface wherein the interior noise levels of the helicopter are significantly reduced.

3. The active noise control system of claim 2 wherein said controller means is further operative in response to said detection signals for providing said command signals to control operation of said actuator means to generate nullifying forces to counteract contaminating forces arising from operation of said actuator means.

4. The active noise control system of claim 1 wherein said modified transmission beam means are mechanically stiffened in their entirety with respect to said at least one high frequency vibration emanating from the main transmission gearbox.

5. The active noise control system of claim 1 wherein said modified transmission beam means are mechanically stiffened only at localized segments thereof adjacent each mounting hardpoint of said modified transmission beam means.

6. The active noise control system of claim 1 wherein said modified transmission beam means comprises port and starboard modified transmission beams.

7. The active noise control system of claim 6 wherein each said port and starboard modified transmission beams are mechanically stiffened in its entirety.

8. The active noise control system of claim 7 wherein said actuator means comprises a first plurality of actuators mounted in combination with said port modified transmission beam and a second plurality of actuators mounted in combination with said starboard modified transmission beam, and wherein said first plurality of actuators is equal in number to said second plurality of actuators.

9. The active noise control system of claim 8 wherein said first plurality of actuators comprises six actuators and wherein said second plurality of actuators comprises six actuators.

10. The active noise control system of claim 6 wherein each said port and starboard modified transmission beams are mechanically stiffened only at localized segments adjacent each mounting hardpoint thereof.

11. The active noise control system of claim 10 wherein said actuator means comprises a first plurality of actuators mounted in combination with each mounting hardpoint of said port modified transmission beam and a second plurality of actuators mounted in combination with each mounting hardpoint of said starboard modified transmission beam, said first plurality of actuators being equal in number to said second plurality of actuators.

12. The active noise control system of claim 11 wherein said first plurality of actuators comprises six actuators and wherein said second plurality of actuators comprises six actuators.

13. The active noise control system of claim 2 wherein said actuator means comprises a plurality of actuators, each of said plurality of actuators being operative to generate a single dimensional counterforce having a predetermined frequency, magnitude, and phase, and wherein each of said single dimensional counterforce acts along a predetermined counterforce axis of said respective actuator.

14. The active noise control system of claim 13 wherein said sensor means further comprises:

a plurality of sensors mounted in combination with said modified transmission beam means adjacent each mounting hardpoint thereof, each of said sensors being mounted in a collinear, spaced apart functional correlation on said predetermined counterforce axis of said respective actuator, each said sensor being operative to detect the magnitude and frequency of a single dimensional component of said at least one high frequency vibration and operative to generate said detection signal representative thereof.

15. The active noise control system of claim 14 wherein said controller means further comprises:

a plurality of controllers functionally interconnecting each of said plurality of sensors with a corresponding one of said actuators, each said controller being operative in response to said detection signal from said respective sensor to provide said command signals to control operation of said respective actuator to generate a single dimensional counterforce having a frequency, magnitude, and phase to effectively nullify said at least one high frequency vibration at said transmission gearbox and airframe interface of said modified transmission beam means.