Device for reducing the vibrations generated by a lift rotor of a rotary-wing aircraft

• US 6,045,090 A
• Filed: 06/12/1997
• Issued: 04/04/2000
• Est. Priority Date: 06/12/1996
• Status: Expired due to Term

• Current Assignee: Airbus Helicopters
• Original Assignee: Eurocopter
• Inventors: Anthoine, Michel Francois, Krysinsky, Thomasz
• Primary Examiner(s): Jordan, Charles T.
• Assistant Examiner(s): DINH, TIEN QUANG
• Application Number:
  US08/873,696
• Time in Patent Office: 1,027 Days
• Field of Search: 244/17.25, 244/17.27, 188/378, 188/379, 188/380, 74/155, 416/500, 416/145
• US Class Current: 244/17.27
• CPC Class Codes: B64C 2027/003 mounted on rotor hub, e.g. a rotary force generator
• CPC Class Codes: B64C 27/001 Vibration damping devices
• CPC Class Codes: F16F 7/1005 characterised by active control of the mass
• CPC Class Codes: F16F 7/116 on metal springs
• CPC Class Codes: Y10T 74/1576 Holding pawl lifter

Abstract

The present invention relates to a device for reducing the vibrations of the rotor of a rotary-wing aircraft, having an oscillating mass (M1), elastically held radially on the hub (4) of the rotor in the vicinity of its axis (X-X) and fixed to an articulated rod (10) substantially longitudinal to said axis (X-X).

According to the invention, said device includes:

an adjustment oscillating mass (M2), mounted so that it can move on the rod (10) and having an adjustment position for which the frequency of the resonator formed by said oscillating masses (M1, M2) is matched to the frequency of said vibrations; and

drive means (18) for bringing the adjustment oscillating mass (M2) into said adjustment position.

Claims

1. A device for reducing the vibrations generated by a lift rotor of a rotary-wing aircraft, said rotor having a shaft which, at least in its upper part comprises a central recess, and said device comprising a main oscillating mass, mounted at an upper part of a hub of said rotor, held radially by elastic means in the vicinity of axis (X-X) of the rotor and fixed to an upper end of a rod which is arranged in said central recess of the shaft of the rotor, substantially longitudinal to the axis (X-X) of said rotor, and which is articulated at its lower end, at a point situated on said axis (X-X) about a directional orthogonal to said axis (X-X), said device further comprises:

an adjustment oscillating mass, mounted so that it can move on said rod and for being brought into and kept in an adjustment position for which the natural frequency of a resonator assembly formed by said main oscillating mass and said adjustment oscillating mass is matched to the frequency of said vibrations of the rotor to be reduced; and

drive means for bringing said adjustment oscillating mass into said adjustment position and for keeping it in this adjustment position.

2. The device as claimed in claim 1, wherein said adjustment oscillating mass is made of a dense material, in a form of a cylinder which is provided with a cylindrical and coaxial through-hole through which said rod can pass.

3. The device as claimed in claim 1, wherein said drive means comprise a motor.

4. The device as claimed in claim 1, wherein said drive means comprise an actuator.

5. The device as claimed in claim 1, further comprising:

at least one sensor for measuring values of at least one parameter representing the vibrations generated by the rotor; and

a computer, receiving the values measured by said sensor, determining as a function of these values the adjustment position of said adjustment oscillating mass, as well as control commands for said drive means to move said adjustment oscillating mass into said adjustment position, and addressing to said drive means the control commands thus determined.

6. The device as claimed in claim 5, wherein said sensor is an accelerometer.

7. The device as claimed in claim 5, wherein said sensor is a velocimeter.

8. The device as claimed in claim 5, wherein said sensor is a displacement sensor.

9. The device as claimed in claim 5, wherein said sensor is a strain gage.

10. The device as claimed in claim 5, wherein said at least one sensor comprises a plurality of sensors, wherein at least a first of said sensors is mounted on a head of the rotor, in order to measure a horizontal acceleration, and wherein at least a second of said sensors is mounted on said main oscillating mass, also in order to measure a horizontal acceleration.

11. The device as claimed in claim 5, wherein said sensor is mounted on a fuselage of the aircraft.

12. The device as claimed in claim 5, wherein said sensor is mounted on a main gearbox of the aircraft.

13. The device as claimed in claim 5, wherein said sensor is mounted on an interface between a main gearbox and a fuselage of the aircraft.

14. The device as claimed in claim 5, wherein, for said vibrations to be reduced having frequency F, the computer defines as the adjustment position, on the rod the position of the adjustment oscillating mass for which its center of gravity is situated, on said rod, at a distance z from the articulated lower end of the rod, said distance z satisfying the expression:

##EQU5## in which;

L is the distance between the center of gravity of the main oscillating mass and said articulated lower end of the rod;

m represents a mass of the main oscillating mass;

μ

represents a mass of the adjustment oscillating mass; and

K represents a stiffness of the elastic means holding the main oscillating mass radially in proximity to the axis (X-X) of the rotor.

15. The device as claimed in claim 14, wherein said sensor detects a rotational speed Ω

of said rotor, which makes it possible directly to determine the frequency F of the vibrations to be reduced of the rotor, by the expression F=b.Ω

, b being a number of blades of said rotor.

16. The device as claimed in claim 5, wherein, in order to determine the adjustment position of the adjustment oscillating mass, said computer moves said adjustment oscillating mass successively along said rod, in order to determine a position that makes it possible to minimize an overall vibrational level in a cockpit of the aircraft, said overall vibrational level NVG being defined by the expression:

##EQU6## in which;

Γ

1 to Γ

n are accelerations measured in said cockpit; and

n is the number of different accelerations measured, the position thus determined representing the adjustment position of the adjustment oscillating mass.