Device for reducing structural vibrations of airfoils

Patent metadata

Field	Value
Publication number	US-9327823-B2
Application number	US-201214124961-A
Country	US
Kind code	B2
Filing date	May 25, 2012
Priority date	Jun 10, 2011
Publication date	May 3, 2016
Grant date	May 3, 2016

Abstract

A device for reducing structural vibrations of airfoils in an aircraft comprises, in the region of the airfoil tips, at least one force generator acting substantially in the direction of movement of the vibrations. This arrangement has the advantage that such a force generator is considerably less susceptible to wear than conventional aerodynamic flaps and therefore effective vibration damping is possible with a reduced outlay on maintenance and greater efficiency.

First claim

The invention claimed is:

1. A device to reduce structural vibrations of airfoils in an aircraft, the device comprising:
at least one force generator arranged in winglets provided on ends of the airfoils, the at least one force generator acting substantially in a direction of movement of the vibrations;
wherein fluid from fuel tanks arranged in an area of airfoil tips is moveable in an oscillatory manner as a vibrating mass of the at least one force generator.

2. The device according to claim 1 , wherein a natural frequency of the at least one force generator is tuned to a first or to a second symmetrical or antisymmetrical flexural vibration in each of the airfoils.

3. The device according to claim 1 , wherein a natural frequency of the at least one force generator is tuned to a mean vibration frequency of a relevant frequency range.

4. The device according to claim 1 , wherein the at least one force generator is designed as a vertically aligned linear motor with a movable primary or secondary part.

5. The device according to claim 4 , wherein the force generator comprises a magnetic or a magnetizable rotor that is enabled to oscillate vertically using at least one stationary supported spring device and a guide surrounded by a stator coil.

6. The device according to claim 4 , wherein the force generator comprises an oscillatable coil and a magnetizable stator.

7. The device according to claim 5 , wherein the rotor is supported on both ends by a double beam spring.

8. The device according to claim 1 , wherein the force generator is controllable as an electric generator.

9. The device according to claim 1 , wherein two or more force generators with different natural frequencies are provided in each winglet.

10. The device according to claim 1 , wherein the fuel tanks are capable of being placed into oscillating motion.

11. The device according to claim 1 , wherein at least two volumetrically variable volume elements are positioned inside the fuel tanks and on one of top and bottom of the fuel tanks, the volumetrically variable volume elements comprise variable oscillating volumes which are reciprocally offset by 180°.

12. The device according to claim 11 , wherein a resonance frequency of the volumetrically variable volume elements is tuned to a natural frequency of a structural vibration to be controlled.

13. The device according to claim 1 , wherein a closed fluid-free hollow body is moveable in an oscillatory manner in a fuel tank.

Assignees

• Storm Stefan
• Maier Rudolf
• Wildschek Andreas
• Airbus Defence & Space Gmbh

Inventors

• Storm Stefan
• Maier Rudolf
• Wildschek Andreas

Classifications

• B64D2045/0085

  Devices for aircraft health monitoring, e.g. monitoring flutter or vibration · CPC title

• B64C2027/004

  using actuators, e.g. active systems · CPC title

• B64C5/08

  mounted on, or supported by, wings · CPC title

• B64C13/16

  actuated automatically, e.g. responsive to gust detectors · CPC title

• B64C9/00 Primary

  Adjustable control surfaces or members, e.g. rudders (trimming stabilising surfaces B64C5/10) · CPC title