Aircraft spring assembly

Patent metadata

Field	Value
Publication number	US-10279896-B2
Application number	US-201615156810-A
Country	US
Kind code	B2
Filing date	May 17, 2016
Priority date	Jun 1, 2015
Publication date	May 7, 2019
Grant date	May 7, 2019

Abstract

An aircraft spring assembly having a spring, an end fitting including a spring engagement formation arranged to be mechanically coupled to an end region of the spring and a coupling formation for coupling the spring assembly to an aircraft anchor point. The coupling formation includes a load bearing surface via which loads from the anchor point can be transmitted into the spring assembly. The assembly further includes an integral damping member provided within the load path between the load bearing surface of the coupling formation and the end region of the spring.

First claim

The invention claimed is:

1. An aircraft spring assembly comprising:
a mechanical spring;
an end fitting including:
a spring engagement formation mechanically coupled to an end region of the spring; and
a coupling formation for coupling the spring assembly to an aircraft anchor point, the coupling formation including a load bearing surface via which loads from the anchor point are transmitted into the spring assembly; and

at least one integral damping member provided within the load path between the load bearing surface of the coupling formation and the end region of the spring in order to decrease the amplitude of mechanical waves induced in the spring due to loads applied to the load bearing surface of the coupling formation.

2. The aircraft spring assembly according to claim 1 , wherein the spring comprises a helical coil spring.

3. The aircraft spring assembly according to claim 1 , wherein the damping member is provided within an axial load path between the load bearing surface of the coupling formation and the end region of the spring in order to decrease the amplitude of longitudinal mechanical waves induced in the spring due to axial loads applied to the load bearing surface of the coupling formation.

4. The aircraft spring assembly according to claim 3 , further comprising one or more guards arranged to contain one of the damping members and having first and second side portions arranged on opposite side of the respective damping member, and configured such that the side portions are movable relative to one another along the axis of the spring to compress the damping member.

5. The aircraft spring assembly according to claim 1 , wherein the coupling formation comprises a cylindrical internal sidewall defining a hole arranged to receive a bush which defines the load bearing surface, and at least one of the damping members is disposed within the hole between the cylindrical internal sidewall and the bush.

6. The aircraft spring assembly according to claim 5 , wherein the bush defines one of the side portions of the guard.

7. The aircraft spring assembly according to claim 1 , wherein the spring engagement formation comprises an annular fitting having an outer surface arranged to engage the spring and a cylindrical internal sidewall defining an axial hole arranged to slidably house a rod, a first end of the rod defines or is coupled to an end stop of greater diameter than the axial hole, and a second end of the rod defines the coupling formation, and at least one of the damping members is mounted between the end stop and annular fitting so as to dampen axial movement of the rod relative to the annular fitting in a first direction.

8. The aircraft spring assembly according to claim 7 , comprising a projection extending radially from the rod between the coupling formation and the annular fitting and wherein at least one of the damping members is mounted between the projection and annular fitting so as to dampen axial movement of the rod relative to the annular fitting in a second direction which is opposite to the first direction.

9. The aircraft spring assembly according to claim 1 , wherein one or more of the damping members each comprises a generally annular member formed from a resilient material which is relatively soft in comparison to the end fitting and/or the spring.

10. The aircraft spring assembly according to claim 9 , wherein the annular member is formed from an elastomer material.

11. The aircraft spring assembly according to claim 1 , wherein one or more of the damping members each comprises a second spring which is less stiff than the first spring.

12. An aircraft landing gear assembly comprising:
an aircraft spring assembly comprising:
a mechanical spring;
a first end fitting including:
a first spring engagement formation arranged to be mechanically coupled to a first end region of the spring, and
a first coupling formation for coupling the spring assembly to an aircraft anchor point, the coupling formation including a load bearing surface via which loads from the anchor point can be are transmitted into the spring assembly;

at least one integral damping member provided within the load path between the load bearing surface of the coupling formation and the end region of the spring in order to decrease the amplitude of mechanical waves induced in the spring due to loads applied to the load bearing surface of the coupling formation; and
a second end fitting;

a first part attached to the first end fitting; and
a second part movably mounted with respect to the first part and attached to the second end fitting, wherein the first and second parts comprise elements of a side stay, a lock link or elements of each.

Assignees

• Safran Landing Systems Uk Ltd

Inventors

• Vatovec Andraz
• Greenwood Paul
• Paddock Andrew

Classifications

• B64C25/26

  Control or locking systems therefor · CPC title

• F16F3/10

  combined with springs made of steel or other material having low internal friction · CPC title

• F03G1/10

  for producing output movement other than rotary, e.g. vibratory · CPC title

• B64C25/20 Primary

  mechanical · CPC title

• F16F3/04

  composed only of wound springs · CPC title