Aircraft landing gear assembly

Patent metadata

Field	Value
Publication number	US-9862483-B2
Application number	US-201615072953-A
Country	US
Kind code	B2
Filing date	Mar 17, 2016
Priority date	Mar 20, 2015
Publication date	Jan 9, 2018
Grant date	Jan 9, 2018

Abstract

An aircraft landing gear assembly includes a fibre composite leaf spring arranged as a down lock spring to make the lock link.

First claim

The invention claimed is:

1. An aircraft landing gear assembly comprising:
a main shock absorbing strut arranged to be movably coupled to an aircraft so as to be movable between a deployed condition, for take-off and landing, and a stowed condition for flight;
a folding stay having a first stay arm coupled to the main shock absorbing strut and a second stay arm movably coupled to the first arm and being arranged to be coupled to the aircraft, the folding stay having a generally aligned condition in which it reacts axial loading thereof to maintain the main shock absorbing strut in the deployed condition and a folded condition in which it permits the main shock absorbing strut to be moved from the deployed condition;
a folding lock link having a first link arm coupled to the stay and a second link arm movably coupled to the first link arm and being arranged to be coupled to another part of the landing gear assembly, the lock link having a generally aligned condition in which it reacts axial loading thereof to maintain the stay in the generally aligned condition and a folded condition in which it permits the stay to be folded; and
a fibre composite leaf spring rigidly coupled to a part of the landing gear assembly and arranged to apply a biasing force to the lock link to urge the lock link to assume the generally aligned condition.

2. The aircraft landing gear assembly according to claim 1 , wherein the leaf spring is elongate, and relatively wide in comparison to its thickness.

3. The aircraft landing gear assembly according to claim 1 , wherein the leaf spring is formed from fibre reinforced composite material with a nominally organic polymer matrix.

4. The aircraft landing gear assembly according to claim 1 , wherein the leaf spring is mounted in a cantilevered manner so as to define a free end which contacts the lock link to urge the lock link to assume the generally aligned condition.

5. The aircraft landing gear assembly according to claim 1 , wherein the leaf spring is rigidly coupled at a first anchor point to a part of the lock link and rigidly coupled at a second anchor point to another part of the landing gear assembly, the leaf spring including a kinked region arranged to enable the effective length of the spring to increase and decrease relative to a default length in order to accommodate articulation movement of the lock link as the landing gear assembly moves between the deployed and stowed conditions.

6. The aircraft landing gear assembly according to claim 1 , further comprising a second leaf spring arranged to provide redundancy should the first spring fail.

7. The aircraft landing gear assembly according to claim 6 , wherein the second spring is substantially identical to the first spring.

8. The aircraft landing gear assembly according to claim 6 , wherein the second spring is arranged in parallel with the first leaf spring and mounted in the same manner.

9. The aircraft landing gear assembly according to claim 6 , wherein the second spring is mounted on a different part or surface of the landing gear assembly in comparison to the first spring.

10. The aircraft landing gear assembly according to claim 9 , wherein, the first spring is rigidly mounted in a cantilevered manner on the stay arm which is arranged to be coupled to the aircraft and the second spring can be rigidly mounted in a cantilevered manner on a cardan joint via which the lock link is coupled to a part of the landing gear assembly other than the stay.

11. The aircraft landing gear assembly according to claim 9 , wherein, the first and second springs are rigidly mounted on opposite sides of the stay arm which is arranged to be coupled to the aircraft, the distal end of each spring being coupled to a bell crank or pivot pin arranged to pivot with the lock link.

12. An aircraft including one or more aircraft landing gear assemblies comprising:
a main shock absorbing strut arranged to be movably coupled to an aircraft so as to be movable between a deployed condition, for take-off and landing, and a stowed condition for flight;
a folding stay having a first stay arm coupled to the main shock absorbing strut and a second stay arm movably coupled to the first arm and being arranged to be coupled to the aircraft, the folding stay having a generally aligned condition in which it reacts axial loading thereof to maintain the main shock absorbing strut in the deployed condition and a folded condition in which it permits the main shock absorbing strut to be moved from the deployed condition;
a folding lock link having a first link arm coupled to the stay and a second link arm movably coupled to the first link arm and being arranged to be coupled to another part of the landing gear assembly, the lock link having a generally aligned condition in which it reacts axial loading thereof to maintain the stay in the generally aligned condition and a folded condition in which it permits the stay to be folded; and
a fibre composite leaf spring rigidly coupled to a part of the landing gear assembly and arranged to apply a biasing force to the lock link to urge the lock link to assume the generally aligned condition.

Assignees

• Safran Landing Systems Uk Ltd

Inventors

• Schmidt Robert Kyle

Classifications

• B64C25/26 Primary

  Control or locking systems therefor · CPC title

• B64C25/58 Primary

  Arrangements or adaptations of shock-absorbers or springs (shimmy-dampers B64C25/50) · CPC title

• B64C25/10

  retractable, foldable, or the like · CPC title