Antivibration suspension device for a mechanical element, and an aircraft

Patent metadata

Field	Value
Publication number	US-9592909-B2
Application number	US-201414477003-A
Country	US
Kind code	B2
Filing date	Sep 4, 2014
Priority date	Sep 6, 2013
Publication date	Mar 14, 2017
Grant date	Mar 14, 2017

Abstract

A suspension device ( 10 ) provided with at least one suspension means ( 20 ) comprising a flapper ( 21 ) performing pendulum motion, the flapper ( 21 ) being provided with a mass support ( 25 ) supporting at least one flapping mass ( 30 ). The mass support ( 25 ) is hinged to a carrier structure ( 2 ) for isolating and to a holder bar ( 15 ) for holding said mechanical assembly. The suspension device ( 10 ) includes at least one force generator ( 70 ), said suspension device ( 10 ) having at least one computer ( 50 ) connected to a measurement system ( 55 ) measuring the levels of vibration, and to said force generator ( 70 ) to regulate said amplitude and said phase actively by controlling the force generator ( 70 ) as a function of at least one measurement signal coming from said measurement system ( 55 ).

First claim

What is claimed is:

1. An antivibratory suspension device for a mechanical assembly, the device comprising:
a flapper performing pendulum motion, the flapper being provided with a mass support that extends from a distal end supporting at least one flapping mass to a proximal end, the proximal end being provided with a first hinge for hinging the mass support to a carrier structure for isolating;
a second hinge for hinging a holder bar of the mechanical assembly to the mass support between the distal end and the proximal end;
at least one dynamic force generator acting on an amplitude and phase of the pendulum motion of a flapper;
a measurement system measuring a vibratory response of the carrier structure; and
a computer in communication with the measurement system and the dynamic force generator,
wherein the computer controls the dynamic force generator to adjust the amplitude and the phase of the flapper as a function of at least one measurement signal coming from the measurement system,
wherein the at least one dynamic force generator includes at least one coil secured to the flapping mass and a magnetic mass, the magnetic mass being directly attached to the flapping mass by a resilient body.

2. The device according to claim 1 , further comprising fastener means for fastening the at least one force generator to the carrier structure.

3. The device according to claim 1 , further comprising a fastener system for fastening at least one force generator to the mechanical assembly.

4. The device according to claim 1 , further comprising a fastener member for fastening at least one dynamic force generator to the flapper.

5. The device according to claim 1 , wherein the at least one dynamic force generator is an electromagnetic actuator comprising a magnetic mass, at least one coil, and an electrical power amplifier connected to the coil and to the computer.

6. The device according to claim 5 , wherein the coil is arranged on the flapping mass.

7. The device according to claim 1 , wherein the measurement system includes attachment means for attachment to the carrier structure.

8. The device according to claim 1 , wherein the at least one dynamic force generator is connected to the flapping mass.

9. The device according to claim 1 , wherein the at least one dynamic force generator includes a piezoelectric member incorporated in the mass support.

10. The device according to claim 1 , wherein the at least one dynamic force generator includes at least one pair of contra-rotating masses carried by the flapping mass.

11. The device according to claim 1 , further comprising a resilient element connected to the flapper in order to provide stiffness between the mechanical assembly and the carrier structure.

12. The device according to claim 1 , further comprising at least two flappers, wherein one force generator is provided for each flapper.

13. The device according to claim 12 further comprising one computer for each force generator.

14. An aircraft having a carrier structure and a mechanical assembly including a lift rotor and a main gearbox driving the lift rotor, the mechanical assembly including at least one holder bar extending from a top end hinged to the main gearbox to a bottom end, wherein the aircraft includes a suspension device according to claim 1 , at least one bottom end of a holder bar being hinged to the second hinge of a suspension means of the suspension device.

15. The aircraft according to claim 14 , wherein each holder bar is hinged to a flapper.

16. An aircraft comprising:
a carrier structure;
a mechanical assembly including a lift rotor and a main gearbox driving the lift rotor, the at least one holder bar extending from a top end hinged to the main gearbox to a bottom end;
an antivibratory suspension device for the mechanical assembly, the antivibratory suspension device including:
a flapper performing pendulum motion, the flapper being provided with a mass support that extends from a distal end supporting at least one flapping mass to a proximal end, the proximal end being provided with a first hinge for hinging the mass support to a carrier structure for isolating;
a second hinge for hinging a holder bar of the mechanical assembly to the mass support between the distal end and the proximal end;
at least one dynamic force generator acting on an amplitude and phase of the pendulum motion of a flapper;
at least one computer connected to the at least one dynamic force generator and to a measurement system measuring a vibratory response of the carrier structure to adjust the amplitude and the phase actively by controlling the at least one dynamic force generator as a function of at least one measurement signal coming from the measurement system,
wherein the at least one dynamic force generator includes at least one coil secured to the flapping mass and a magnetic mass, the magnetic mass being directly attached to the flapping mass by a resilient body, with at least one bottom end of the holder bar being hinged to the second hinge of a suspension means of the suspension device.

17. An aircraft comprising:
a carrier structure;
a mechanical assembly including a lift rotor and a main gearbox driving the lift rotor;
a holder bar hinged at a top end to the main gearbox and extending to a bottom end;
an antivibratory suspension device for the mechanical assembly, the antivibratory suspension device including:
a flapper hinged to the carrier structure at a proximal end to act in pendulum motion, the flapper having at least one flapping mass supported on a distal end;
a second hinge for hinging the at least one holder bar to the flapper;
a dynamic force generator acting on an amplitude and phase of the pendulum motion of a flapper;
a measurement system measuring a vibratory response of the carrier structure;
a computer in communication with the measurement system and the dynamic force generator, wherein the computer controls the dynamic force generator to adjust the amplitude and the phase of the flapper based on the measured vibratory response of the carrier structure,

wherein the dynamic force generator includes at least one coil secured to the flapping mass and a magnetic mass, the magnetic mass being directly attached to the flapping mass by a resilient body.

18. The aircraft according to claim 17 , wherein a center of mass of the flapper is located between the second hinge and the distal end.

Assignees

• Airbus Helicopters

Inventors

• Cranga Paul
• Eberhard Alain
• Rodriguez Jonathan
• Rogier Benoit

Classifications

• B64C2027/005

  using suspended masses · CPC title

• B64C2027/002

  mounted between the rotor drive and the fuselage · CPC title

• B64C27/001 Primary

  Vibration damping devices · CPC title

• B64D27/404

  Suspension arrangements specially adapted for supporting vertical loads · CPC title

• F16F15/02 Primary

  Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems ({F16F15/005 takes precedence } ; layered products B32B; suppression of vibration in ships B63; {relieving load on bearings, using magnetic means F16C39/06}) · CPC title