METHOD FOR DAMPING REAR EXTENSION ARM VIBRATIONS OF ROTORCRAFT AND ROTORCRAFT WITH A REAR EXTENSION ARM VIBRATION DAMPING DEVICE

• US 20080173754A1
• Filed: 10/05/2007
• Published: 07/24/2008
• Est. Priority Date: 02/03/2003
• Status: Abandoned Application

• Current Assignee: Airbus Deutschland GmbH (Airbus SE)
• Original Assignee: Airbus Deutschland GmbH (Airbus SE)
• Inventors: Strehlow, Henning, Duerr, Johannes K., Rottmayr, Heiner, Zaglauer, Helmut W.
• Application Number:
  US11/868,061
• Publication Number:
  US 20080173754A1
• Time in Patent Office: Days
• US Class Current: 244/17.13
• CPC Class Codes: B64C 2027/8254 Shrouded tail rotors, e.g. "Fenestron" fans
• CPC Class Codes: B64C 2220/00 Active noise reduction systems
• CPC Class Codes: B64C 27/001 Vibration damping devices
• CPC Class Codes: F16F 15/02 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

Abstract

A method for damping vibrations in a tail boom of a rotary-wing aircraft includes the steps of detecting tail boom vibrations induced by external vibration excitation, and generating and introducing strains into the tail boom based on the detected tail boom vibrations. The strains are applied over a surface area and are out-of-phase with respect to the detected tail boom vibrations so as to damp the externally excited induced tail boom vibrations. In addition, a rotary-wing aircraft, includes a fuselage, a cockpit area integrated into the fuselage, a tail boom arranged on the fuselage and a tail boom vibration-damping device. The vibration-damping device has at least one sensor element configured to detect tail boom vibrations induced by external vibration excitation and at least one actuator configured to generate and introduce strains into the tail boom that are out-of-phase with respect to the induced tail boom vibrations, the actuator being functionally coupled to the sensor element, engaging with a tail boom structure at one side of the tail boom, and forming a flat-surfaced bond with the tail boom.

Claims

1. A method for damping vibrations in a tail boom of a rotary-wing aircraft, the method comprising:

detecting tail boom vibrations induced by external vibration excitation; and

generating and introducing strains into the tail boom based on the detected tail boom vibrations, the strains being applied over a surface area and being out-of-phase with respect to the detected tail boom vibrations; and

damping the externally excited induced tail boom vibrations.

2. The method as recited in claim 1, wherein the rotary-wing aircraft is a helicopter.

3. The method as recited in claim 1, wherein the introducing of the strains is performed at locations of the tail boom having a highest structural strain energy.

4. The method as recited in claim 1, wherein the introducing of the strains is performed in a vicinity of locations of the tail boom wherein a bending line of the tail boom exhibits a discontinuity site.

5. The method as recited in claim 1, wherein the detecting of the tail boom vibrations is performed by measuring induced structural strains of the tail boom.

6. The method as recited in claim 1, wherein the detecting of the tail boom vibrations is performed by measuring vibration velocities of the tail boom.

7. The method as recited in claim 1, wherein the tail boom vibrations are detected at the tail boom.

8. The method as recited in claim 1, wherein the tail boom vibrations are detected in at least one of a cockpit area and a passenger cabin area of the rotary-wing aircraft.

9. The method as recited in claim 1, wherein the introducing of the strains includes introducing the strains into the tail boom with an out-of-phase strain velocity.

10. The method as recited in claim 1, wherein the detecting includes detecting a lateral eigenform of the tail boom vibrations.

11. The method as recited in claim 1, wherein the detecting includes detecting a vertical eigenform of the tail boom vibrations.

12. A rotary-wing aircraft, comprising:

a fuselage;

a cockpit area integrated into the fuselage;

a tail boom arranged on the fuselage; and

a tail boom vibration-damping device having at least one sensor element configured to detect tail boom vibrations induced by external vibration excitation and at least one actuator configured to generate and introduce strains into the tail boom that are out-of-phase with respect to the induced tail boom vibrations, the actuator being functionally coupled to the sensor element, engaging with a tail boom structure at one side of the tail boom, and forming a flat-surfaced bond with the tail boom.

13. The rotary-wing aircraft as recited in claim 12, wherein the rotary-wing aircraft is a helicopter.

14. The rotary-wing aircraft as recited in claim 12, wherein the tail boom vibration-damping device includes at least two actuators that engage with the tail boom structure on opposite sides of the tail boom relative to a cross section of the tail boom and form a flat-surfaced bond with the tail boom, the actuators being functionally coupled to the sensor element, for generating and introducing the strains into the tail boom.

15. The rotary-wing aircraft as recited in claim 12, wherein the at least one actuator is arranged on only one side of the tail boom or on only one side of a transition area between the tail boom and an add-on component, said side being selected from a group of sides consisting of a top side, a bottom side, a left-hand side and a right-hand side of the tail boom.

16. The rotary-wing aircraft as recited in claim 12, wherein the at least one actuator includes at least two actuators, one of the at least two actuators being disposed on a left-hand side and another of the at least two actuators being disposed on a right-hand side of one of the tail boom and a transition area between the tail boom and an add-on component.

17. The rotary-wing aircraft as recited in claim 12, wherein the at least one actuator includes at least two actuators, one of the at least two actuators being disposed on a top side and another of the at least two actuators being disposed on a bottom side of one of the tail boom and a transition area between the tail boom and an add-on component.

18. The rotary-wing aircraft as recited in claim 12, wherein the at least one actuator is applied onto the tail boom structure.

19. The rotary-wing aircraft as recited in claim 12, wherein the at least one actuator is integrated into the tail boom structure.

20. The rotary-wing aircraft as recited in claim 12, wherein the tail boom is one of pre-tensioned and pre-bent essentially in a first direction of the vibration to be damped and is connected to the at least one actuator, the at least one actuator being actuatable in a second direction opposite to the first direction.