Active vibration control system for helicopter with improved actustor placement

• US 6,467,723 B1
• Filed: 10/10/2000
• Issued: 10/22/2002
• Est. Priority Date: 10/10/2000
• Status: Expired due to Fees

• Current Assignee: Lord Corporation (Parker-Hannifin Corporation)
• Original Assignee: Lord Corporation (Parker-Hannifin Corporation)
• Inventors: Norris, Mark A., Rossetti, Dino J., Billoud, Guy D.
• Primary Examiner(s): Barefoot, Galen L.
• Application Number:
  US09/686,009
• Time in Patent Office: 742 Days
• Field of Search: 244/1.N, 244/17.27, 244/17.13, 244/17.11, 181/33, 188/378, 416/500, 381/71.4, 381/71.9, 381/71.12
• US Class Current: 244/17.11
• CPC Class Codes: B64C 2027/004 using actuators, e.g. active systems
• CPC Class Codes: B64C 27/001 Vibration damping devices

Abstract

An aircraft has a fuselage that defines an interior cabin and an exterior; a first housing located along one side of the fuselage exterior; a second housing located along the second side of the fuselage exterior; and an active vibration control system for limiting fuselage vibration, the vibration control system comprising a plurality of sensors located in the cabin; a controller in signal receiving relation with the sensor means; first actuator means located in the first housing and second actuator means located in the second housing and wherein the actuator means are in signal receiving relation with the controller.

Claims

1. An aircraft comprising:

g) a fuselage that defines interior cockpit and cabin sections and an exterior;

h) at least one housing along the exterior of the fuselage; and

i) an active vibration control system for limiting fuselage vibration, the system comprising;

(i) sensor means for sensing the vibration;

(ii) controller means in signal receiving relation with the sensor means; and

(iii) actuator means located in the at least one housing, said actuator means being in signal receiving relation with controller means, said actuator being actuated by signals received by said actuator means from said controller as required to cancel a vibratory disturbance having a magnitude within a predetermined range of frequencies and occurring at one of a plurality of predetermined locations in the aircraft fuselage.

2. The aircraft as claimed in claim 1 wherein the aircraft is a helicopter.

3. The aircraft as claimed in claim 1 wherein there are two housings.

4. The aircraft as claimed in claim 1 wherein each of the at least one housing comprises a stub wing.

5. The aircraft as claimed in claim 3 wherein there are two stub wings, one on each side of the fuselage.

6. The aircraft as claimed in claim 1 wherein there are two stub wings, an actuator being located in each stub wing.

7. The aircraft as claimed in claim 1 wherein the active vibration control system sensor means is comprised of a plurality of accelerometers.

8. The aircraft as claimed in claim 3 wherein the sensor means are located in the cockpit and cabin sections.

9. The aircraft as claimed in claim 7 wherein the sensor means is comprised of two accelerometers located in the cockpit section, two accelerometers located in the cabin adjacent to the housings and one accelerometer located in the mid cabin away from the housings.

10. The aircraft as claimed in claim 1 wherein the sensor means comprises a plurality of accelerometers located in the interior cabin.

11. The aircraft as claimed in claim 1 wherein the actuator means is a rotary actuator.

12. The aircraft as claimed in claim 1 wherein the actuator means is comprised of a mass suspended by spring means.

13. The aircraft as claimed in claim 12 wherein the spring means is a plurality of leaf springs.

14. The aircraft as claimed in claim 1 wherein the actuator mass is comprised of a first mass, a second mass, a housing enclosing the masses;

and electromagnetic coil substantially surrounding the first and second masses; and

first and second spring members respectively joining the first and second masses to the housing.

15. The aircraft as claimed in claim 1 wherein the actuator means provides vibration cancellation at harmonics of the vibratory frequency of the rotor.

16. The aircraft as claimed in claim 1 wherein the actuator means is comprised of a linear actuator.