Method for operating a landing gear and an aircraft including the landing gear

Patent metadata

Field	Value
Publication number	US-10654563-B2
Application number	US-201916368322-A
Country	US
Kind code	B2
Filing date	Mar 28, 2019
Priority date	Sep 2, 2016
Publication date	May 19, 2020
Grant date	May 19, 2020

Abstract

A method for operating a landing gear. The method includes extending an actuator to apply a force to a crank link of a toggle lock mechanism causing a mechanical unlocking of a second lock link from a fully extended position, retracting the actuator to rotate the toggle lock mechanism about a toggle lock pivot axis of a first lock link, causing rotation of the second lock link that is rotatably coupled to the first lock link so that the second lock link folds relative to the first lock link in a second rotation direction, and a toggle link of the toggle lock mechanism rotates relative to the second lock link, in the first rotation direction opposite the second rotation direction, to rotate the second lock link to a fully retracted position of the second lock link relative to the first lock link.

First claim

What is claimed is:

1. A method for operating a landing gear, the method comprising:
extending an actuator to apply a force to a crank link of a toggle lock mechanism to rotate the toggle lock mechanism in a first rotation direction against a biasing force of at least one biasing member causing a mechanical unlocking of a second lock link from a fully extended position and causing rotation of the second lock link away from the fully extended position;
retracting the actuator to rotate the toggle lock mechanism about a toggle lock pivot axis of a first lock link, causing rotation of the second lock link that is rotatably coupled to the first lock link so that
the second lock link folds relative to the first lock link in a second rotation direction, and
a toggle link of the toggle lock mechanism rotates relative to the second lock link, in the first rotation direction opposite the second rotation direction, to rotate the second lock link to a fully retracted position of the second lock link relative to the first lock link; and

wherein:
the first lock link and the second lock link are distinct from a landing gear shock strut of the landing gear, and
the toggle link couples the crank link to the second lock link, the actuator is coupled to both the first lock link and the crank link, and the at least one biasing member is coupled to both the first lock link and the crank link.

2. The method of claim 1 , wherein the biasing force applied to the crank link of the toggle lock mechanism with the at least one biasing member is applied with at least two biasing members.

3. The method of claim 1 , wherein the biasing force applied to the crank link of the toggle lock mechanism with the at least one biasing member is applied with but one set of biasing members on a common side of the first lock link.

4. The method of claim 1 , wherein the biasing force applied to the crank link of the toggle lock mechanism with the at least one biasing member is applied with but one set of biasing members located on a side of the first lock link opposite a sweep path of the second lock link.

5. The method of claim 1 , wherein retracting the actuator applies a force to the crank link on a first end of the crank link and the force applied to the crank link by the at least one biasing member is applied to a second end of the crank link, where the first and second ends of the crank link are located on opposite sides of a toggle lock pivot axis.

6. The method of claim 1 , wherein the crank link and the toggle link of the toggle lock mechanism are configured to fold in a direction opposite the second rotation direction.

7. The method of claim 1 , wherein the mechanical unlocking of the second lock link from the fully extended position is caused by releasing an over center locking of the toggle link and crank link.

8. The method of claim 1 , further comprising transitioning the at least one biasing member from a substantially relaxed configuration to an extended configuration and back to a substantially relaxed configuration during retraction of the second lock link from the fully extended position to a fully retracted position.

9. The method of claim 8 , wherein the extended configuration is about 75% to about 100% of a length of the at least one biasing member at full rated extension of the at least one biasing member.

10. The method of claim 9 , wherein the extended configuration occurs at about 80% to about 90% of a sweep angle of the second lock link from the fully retracted position to the fully extended position.

11. An aircraft comprising:
a landing gear having a landing gear shock strut; and
a landing gear lock assembly for the landing gear, the landing gear lock assembly comprising:
a first lock link having a first end and a second end;
a second lock link having a first end and a second end, the first end of the second lock link being rotatably coupled to the second end of the first lock link so that the first and second lock links unfold relative to each other in a first rotation direction, where both the first lock link and the second lock link are distinct from the landing gear shock strut; and
a toggle lock mechanism having a crank link and a toggle link rotatably coupled to each other at a toggle link axis, the toggle link being rotatably coupled to the second lock link, and the crank link being rotatably coupled to the first lock link so that the toggle link rotates relative to the second lock link, in a second rotation direction opposite the first rotation direction, to mechanically lock the second lock link in a fully extended position.

12. The aircraft of claim 11 , further comprising at least one biasing member coupled to both the first lock link and the crank link.

13. The aircraft of claim 12 , wherein the at least one biasing member comprises two or more biasing members located on a common side of the first lock link.

14. The aircraft of claim 12 , wherein the at least one biasing member is in a substantially relaxed state when the second lock link is in a fully retracted position.

15. The aircraft of claim 12 , wherein the at least one biasing member is in a substantially relaxed state when the second lock link is in the fully extended position.

16. The aircraft of claim 11 , further comprising at least one actuator having a first end coupled to the first lock link and a second end coupled to the crank link.

17. The aircraft of claim 16 , wherein the crank link has a first end and a second end and a toggle lock pivot axis disposed between the first end and second end of the crank link, the crank link being rotatably coupled to the first lock link about the toggle lock pivot axis and the at least one actuator is coupled to the first end of the crank link, the landing gear lock assembly further comprises at least one biasing member having a first end coupled to the first lock link and a second end coupled to the second end of the crank link.

18. The aircraft of claim 16 , wherein the first lock link includes a recess, the at least one actuator being disposed within the recess.

19. The aircraft of claim 11 , wherein the landing gear lock assembly comprises a self-contained locking assembly functionally mounted to an aircraft by only the first lock link and second lock link.

20. The aircraft of claim 11 , wherein the crank link and the toggle link of the toggle lock mechanism are configured to unfold in a direction opposite the first rotation direction.

Assignees

• Boeing Co

Inventors

• Mellor Mitchell
• Hansen Brian

Classifications

• B64C25/12

  sideways · CPC title

• B64C25/26 Primary

  Control or locking systems therefor · CPC title

• B64C25/20

  mechanical · CPC title

• F16H21/06

  which can be made ineffective when desired · CPC title

• F16H21/44

  for conveying or interconverting oscillating or reciprocating motions · CPC title