Aircraft spring assembly

Patent metadata

Field	Value
Publication number	US-9783287-B2
Application number	US-201614987085-A
Country	US
Kind code	B2
Filing date	Jan 4, 2016
Priority date	Jan 5, 2015
Publication date	Oct 10, 2017
Grant date	Oct 10, 2017

Abstract

An aircraft spring assembly includes a helical spring having a hollow core. A polymer damping member is confined within the core and is narrower than the internal spring diameter so as to be free to move along the core.

First claim

The invention claimed is:

1. An aircraft spring assembly comprising:
a helical spring having a first end region and a second end region and a hollow core defined between the first end region and the second end region;
a first anchor element coupled to the first end region;
a second anchor element coupled to the second end region; and
a polymer damping member provided within the hollow core, the diameter of the damping member being less than the diameter of the spring such that the damping member is freely movable along the hollow core, the length of the damping member being greater than the distance between adjacent coils of the spring when the spring is in a fully extended condition such that the damping member is confined to the hollow core as the spring moves between extended and contracted conditions.

2. The aircraft spring assembly according to claim 1 , wherein the damping member comprises an elastomer material.

3. The aircraft spring assembly according to claim 1 , wherein the damping member has a mass that is at least 0.05 times the mass of the spring.

4. The aircraft spring assembly according to claim 1 , wherein the damping member includes a core formed from a relatively dense material in comparison to the polymer.

5. The aircraft spring assembly according to claim 1 , wherein the length of the damping member is less than the axial distance between inner axial surfaces of the anchor elements when the spring is in a contracted state.

6. The aircraft spring assembly according to claim 5 , wherein the contracted state is a natural contracted state and/or a fully contracted state.

7. An aircraft landing gear assembly comprising: an aircraft spring assembly comprising: a helical spring having a first end region and a second end region and a hollow core defined between the first end region and the second end region; a first anchor element coupled to the first end region, a second anchor element coupled to the second end region, and a polymer damping member provided within the hollow core, the diameter of the damping member being less than the diameter of the spring such that the damping member is freely movable along the hollow core, the length of the damping member being greater than the distance between adjacent coils of the spring when the spring is in a fully extended condition such that the damping member is confined to the hollow core as the spring moves between extended and contracted conditions; a first part attached to the first anchor element; and a second part movably mounted with respect to the first part and attached to the second anchor element.

8. The aircraft landing gear assembly according to claim 7 , wherein the first part is a stay arm and the second part is a lock link arm, the spring serving as a down lock spring.

9. An aircraft including one or more aircraft landing gear assemblies comprising: an aircraft spring assembly comprising: a helical spring having a first end region and a second end region and a hollow core defined between the first end region and the second end region, a first anchor element coupled to the first end region, a second anchor element coupled to the second end region, and a polymer damping member provided within the hollow core, the diameter of the damping member being less than the diameter of the spring such that the damping member is freely movable along the hollow core, the length of the damping member being greater than the distance between adjacent coils of the spring when the spring is in a fully extended condition such that the damping member is confined to the hollow core as the spring moves between extended and contracted conditions; a first part attached to the first anchor element; and a second part movably mounted with respect to the first part and attached to the second anchor element.

10. An aircraft assembly including an aircraft spring assembly comprising: a helical spring having a first end region and a second end region and a hollow core defined between the first end region and the second end region; a first anchor element coupled to the first end region; a second anchor element coupled to the second end region; and a polymer damping member provided within the hollow core, the diameter of the damping member being less than the diameter of the spring such that the damping member is freely movable along the hollow core, the length of the damping member being greater than the distance between adjacent coils of the spring when the spring is in a fully extended condition such that the damping member is confined to the hollow core as the spring moves between extended and contracted conditions.

Assignees

• Safran Landing Systems Uk Ltd

Inventors

• Hilliard Matthew

Classifications

• F16F2222/08

  Inertia · CPC title

• B64C25/001

  Devices not provided for in the groups B64C25/02 - B64C25/68 · CPC title

• F16F7/10

  using inertia effect (F16F13/108, F16F13/22, F16F15/10, F16F15/22 take precedence; stabilising vehicle bodies by means of movable masses B62D37/04; protection of buildings against vibrations or shocks by mass dampers E04H9/0215; arrangements or devices for damping mechanical oscillations of power lines H02G7/14) · CPC title

• F16F1/128 Primary

  with motion-limiting means, e.g. with a full-length guide element or ball joint connections; with protective outer cover (F16F1/121 takes precedence) · CPC title

• B64C25/10

  retractable, foldable, or the like · CPC title