Antivibration kit-of-parts and parts therefor, airfoil structure and aircraft provided therewith

Patent metadata

Field	Value
Publication number	US-11840336-B2
Application number	US-202017424808-A
Country	US
Kind code	B2
Filing date	May 26, 2020
Priority date	May 28, 2019
Publication date	Dec 12, 2023
Grant date	Dec 12, 2023

Abstract

To reduce vibration of movable airfoil structures, such as rudders, elevators, and ailerons, a spring device, a leaf spring for example, is mounted to an airfoil mounting structure, such as a vertical tail plane, horizontal tail plane or the wings, such that the spring device exerts a force on a cam device, which transforms the spring force into an airfoil torque. The airfoil torque is applied to the airfoil structure and thus reduces a risk of vibration. The cam device is configured to redirect the spring force such that when the airfoil structure is moved in a first direction, torque decreases and when moved in the opposite second direction the torque is zero.

First claim

The invention claimed is:

1. An apparatus configured to reduce vibration of an airfoil structure, the airfoil structure being movably attachable to an aircraft, wherein the apparatus comprises:
a spring device configured to generate a spring force due to deflection from a spring neutral position of the spring device; and
a cam device configured to transform the spring force into an airfoil torque while, when both the spring device and the cam device are in an operating condition, the cam device contacts the spring device, and the cam device is configured to apply the airfoil torque to the airfoil structure while, when both the spring device and the cam device are in the operating condition, the cam device is operatively coupled to the airfoil structure,
wherein the cam device comprises a cam device mounting portion configured to mount the cam device to the airfoil structure and a hinge portion defining an axis of rotation about which the cam device is configured to rotate, and,
wherein the cam device further comprises a lever portion that extends from the hinge portion and that is configured to contribute in transforming the spring force into an airfoil torque, a head portion that is adjacent to the lever portion and spaced apart from the hinge portion via the lever portion, a cam that is formed on the head portion and the cam is formed on a single lateral side of the cam device and a single front side with respect to a longitudinal direction of the cam device.

2. The apparatus according to claim 1 , wherein the cam device is configured to at least one of:
be rotatable about the axis of rotation, so as to transform the spring force into the airfoil torque;
transform the spring force into the airfoil torque being nonzero, when the cam device is moved from a cam device neutral position in a first direction but not another direction;
transform the spring force into the airfoil torque being zero when the cam device is moved from a cam device neutral position in a second direction but not another direction, although the spring device stays in contact with the cam device; or
transform the spring force into the airfoil torque being zero by directing the spring force to point towards the axis of rotation.

3. The apparatus according to claim 1 , wherein, when both the spring device and the cam device are in the operating condition,
the spring device is deflected when the cam device is in a cam device neutral position;
the deflection of the spring device decreases when the cam device is moved from a cam device neutral position in a first direction but not another direction;
the deflection of the spring device stays the same, when the cam device is moved from a cam device neutral position in a second direction but not another direction; or
the deflection of the spring device initially increases and subsequently stays the same, when the cam device is moved from a cam device neutral position in a second direction but not another direction.

4. The apparatus according to claim 1 , wherein the spring device comprises a leaf spring configured to generate the spring force.

5. The apparatus according to claim 1 , wherein the leaf spring
comprises a plurality of leaf spring layers stacked on each other in a sliding manner;
has a fixed end portion, at which the leaf spring layers are fixed to each other;
has a free end portion, at which the leaf spring layers are free to slide relative to each other;
comprises a friction reducing member sandwiched between two neighboring leaf spring layers; or
has a leaf spring bracket configured to support the leaf spring layers in a sliding manner.

6. The apparatus according to claim 5 , wherein at least one of:
the spring device comprises a contact portion arranged to contact the cam device, so as to transfer the spring force to the cam device; or
the spring device comprises a reinforcement member configured to reinforce the spring device.

7. The apparatus according to claim 6 ,
wherein the contact portion is arranged at the free end or the leaf spring bracket;
wherein the contact portion comprises a roller, which contacts the cam device; or
wherein the reinforcement member is arranged at the fixed end portion.

8. The apparatus according to claim 1 , wherein the cam device comprises a cam portion configured to direct the spring force in such a manner that, when the cam device is in the operating condition, the spring force is directed in the same direction relative to the aircraft for a majority of a movement of the cam device relative to the aircraft.

9. An airfoil structure arrangement for an aircraft, the airfoil structure arrangement comprising an airfoil mounting structure, an airfoil structure movably mounted to the airfoil mounting structure, and the apparatus according to claim 1 , wherein the spring device is mounted to the airfoil structure and the cam device is mounted to the airfoil structure.

10. The airfoil structure arrangement according to claim 9 , wherein at least one of:
the cam portion comprises an urging cam portion configured to direct the spring force such that the spring force is directed parallel to a lateral direction of the aircraft; or
the cam portion comprises a neutral cam portion configured to direct the spring force such that the spring force is directed towards an axis of rotation of the cam device.

11. The airfoil structure arrangement according to claim 10 , wherein the spring force is directed in a left-right direction.

12. The airfoil structure arrangement according to claim 10 , wherein the spring force is directed in a top-bottom direction.

13. The airfoil structure arrangement according to claim 10 , wherein the airfoil mounting structure comprises at least one of a wing, a vertical tail plane, or a horizontal tail plane, and wherein the airfoil structure comprises a control surface or high lift device.

14. An aircraft, in particular airplane, comprising an airfoil structure according to claim 9 .

15. A cam device for use in an apparatus configured to reduce vibration of an airfoil structure, the airfoil structure being movably attachable to an aircraft, wherein the cam device comprises:
a cam device mounting portion configured to mount the cam device to an airfoil structure,
a hinge portion defining an axis of rotation about which the cam device is rotatable, and
a cam portion configured to direct a spring force exerted on the cam portion in such a manner that, when the cam device is in the operating condition, the spring force is directed in the same direction relative aft,
wherein the cam device further comprises a lever portion that extends from the hinge portion and that is configured to contribute in transforming the spring force into an airfoil torque, a head portion that is adjacent to the lever portion and spaced apart from the hinge portion via the lever portion, a cam that is formed on the head portion and the cam is formed on a single lateral side of the cam device and a single front side with respect to a longitudinal direction of the cam device.

16. An apparatus configured to reduce vibration of an airfoil structure, the airfoil structure being movably attachable to an aircraft, wherein the apparatus comprises:
a spring device configured to generate a spring force due to deflection from a spring neutral position of the spring device; and
a cam device configured to transform the spring force into an airfoil torque while, when both the spring device and the cam device are in an operating condition, the cam device contacts the spring device, and the cam device is configured to apply the airfoil t

Assignees

• Airbus Operations Gmbh

Inventors

• Bertolini Ivano
• Lüttmann Henrik
• Westbroek Wim

Classifications

• B64C9/02 Primary

  Mounting or supporting thereof · CPC title

• B64C13/32

  using cam mechanisms · CPC title

• F16F1/3686

  End mountings · CPC title

• F16F2238/022

  leaf-like, e.g. of thin, planar-like metal · CPC title

• F16F3/023 Primary

  composed only of leaf springs · CPC title