UNIFIED CONTROL OF MULTIPLE ACTIVE SYSTEMS FOR HELICOPTER VIBRATION SUPPRESSION

• US 20170088257A1
• Filed: 09/30/2015
• Published: 03/30/2017
• Est. Priority Date: 09/30/2015
• Status: Abandoned Application

• Current Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Original Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Inventors: Singh, Rupinder, Heverly, David E. II, Lee, Taeoh, Smith, Michael
• Application Number:
  US14/871,615
• Publication Number:
  US 20170088257A1
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64C 2027/002 mounted between the rotor drive and the fuselage
• CPC Class Codes: B64C 2027/004 using actuators, e.g. active systems
• CPC Class Codes: B64C 2027/005 using suspended masses
• CPC Class Codes: B64C 27/001 Vibration damping devices
• CPC Class Codes: B64C 27/06 with single rotor
• CPC Class Codes: F01D 21/003 Arrangements for testing or measuring for measuring vibrations G01H
• CPC Class Codes: F01D 25/28 Supporting or mounting arrangements, e.g. for turbine casing

Abstract

A vibration control system for a rotorcraft includes at least one of an integrated actuator and an intermediate actuator associated with a first source of vibration, a sensor configured to sense vibration from the first source of vibration, a dedicated actuator configured for association with a fuselage, and a controller configured to receive information from the sensor and configured to control the dedicated actuator and the at least one of the integrated actuator and the intermediate actuator.

Claims

1. A vibration control system for a rotorcraft, comprising:

at least one of an integrated actuator and an intermediate actuator associated with a first source of vibration;

a sensor configured to sense vibration from the first source of vibration;

a dedicated actuator configured for association with a fuselage; and

a controller configured to receive information from the sensor and configured to control the dedicated actuator and the at least one of the integrated actuator and the intermediate actuator.

2. The vibration control system of claim 1, wherein the first source of vibration comprises a main rotor system.

3. The vibration control system of claim 1, wherein the integrated actuator is configured to affect operation of a rotor system.

4. The vibration control system of claim 1, wherein the intermediate actuator is associated with a pylon mounting system.

5. The vibration control system of claim 1, wherein the dedicated actuator comprises an inertial force generator.

6. The vibration control system of claim 1, wherein the first source of vibration comprises an anti-torque system.

7. The vibration control system of claim 1, wherein the first source of vibration comprises an engine.

8. A method, comprising:

operating a first source of vibration of a rotorcraft;

sensing vibration attributable to the first source of vibration;

to reduce at least one of a vibration and an audible noise associated with a fuselage of the rotorcraft, operating a controller to receive the sensed vibration, control at least one of an integrated actuator associated with the first source of vibration and an intermediate actuator associated with the first source of vibration, and control at least one of (1) an integrated actuator associated with a second source of vibration and an intermediate actuator associated with the second source of vibration and (2) a dedicated actuator associated with a fuselage of the rotorcraft.

9. The method of claim 8, wherein the first source of vibration comprises a main rotor system of the rotorcraft.

10. The method of claim 8, wherein the integrated actuator associated with the first source of vibration is configured to affect vibration produced by a main rotor system.

11. The method of claim 8, wherein the intermediate actuator associated with the first source of vibration is further associated with a pylon mount system.

12. The method of claim 8, wherein the second source of vibration comprises an anti-torque system of the rotorcraft.

13. The method of claim 8, wherein the second source of vibration comprises an engine of the rotorcraft.

14. The method of claim 8, wherein the dedicated actuator is further associated with a mass that is movable relative to the fuselage.

15. The method of claim 14, wherein the dedication actuator comprises an inertial force generator.

16. A helicopter, comprising:

a main rotor system;

a fuselage;

a pylon mount system connected between the main rotor system and the fuselage;

at least two of an integrated actuator associated with the main rotor system, an intermediate actuator associated with the main rotor system, and a dedicated actuator associated with the fuselage;

a sensor configured to sense vibration generated by the main rotor system; and

a controller configured to receive information from the sensor and configured to control at least two of the integrated actuator associated with the main rotor system, the intermediate actuator associated with the main rotor system, and the dedicated actuator associated with the fuselage.

17. The helicopter of claim 16, wherein the dedicated actuator comprises an inertial force generator.

18. The helicopter of claim 16, wherein the sensor comprises an accelerometer or a strain gauge.

19. The helicopter of claim 16, wherein the intermediate actuator is further associated with the pylon mounting system.

20. The helicopter of claim 16, wherein the controller is configured to control each of the integrated actuator associated with the main rotor system, the intermediate actuator associated with the main rotor system, and the dedicated actuator associated with the fuselage.