Upper side stay with monolithic unlock actuator

Patent metadata

Field	Value
Publication number	US-11230370-B2
Application number	US-201916255483-A
Country	US
Kind code	B2
Filing date	Jan 23, 2019
Priority date	Jan 23, 2019
Publication date	Jan 25, 2022
Grant date	Jan 25, 2022

Abstract

An upper side brace for use in landing gear includes a main body having a mounting end configured to be proximal to an aircraft and a lower end configured to be proximal to a lower side brace. The upper side brace further includes an unlock actuator cylinder formed monolithic with the main body and configured to house a piston to form an unlock actuator.

First claim

What is claimed is:

1. An upper side brace for use in landing gear, the upper side brace comprising:
a main body having a mounting end configured to be proximal to an aircraft and a lower end configured to be proximal to a lower side brace; and
an unlock actuator cylinder formed monolithic with the main body and configured to house a piston to form an unlock actuator, wherein:
the main body defines fluid channels in fluidic communication with the unlock actuator cylinder and configured to port fluid at least one of to or from the unlock actuator cylinder, and
the main body further defines a lock hinge connector located between the mounting end and the lower end and configured to be pivotably coupled to an actuator link such that the actuator link is located between the lock hinge connector and the piston.

2. The upper side brace of claim 1 , wherein the mounting end of the main body defines a mount hinge connector configured to pivotably couple to a mount.

3. The upper side brace of claim 2 , wherein the lower end of the main body defines a lower hinge connector configured to pivotably couple to the lower side brace.

4. The upper side brace of claim 1 , wherein the main body further defines a spring aperture configured to be coupled to a spring.

5. The upper side brace of claim 1 wherein the unlock actuator cylinder defines a tube configured to receive the piston of the unlock actuator.

6. A side brace assembly for use in landing gear, the side brace assembly comprising:
an actuator link;
a lower side brace; and
an upper side brace having a main body with a mounting end configured to be proximal to an aircraft and a lower end configured to be coupled to the lower side brace, and an unlock actuator cylinder formed monolithic with the main body and configured to house a piston to form an unlock actuator, wherein:
the main body of the upper side brace defines fluid channels in fluidic communication with the unlock actuator cylinder and configured to port fluid at least one of to or from the unlock actuator cylinder, and
the main body further defines a lock hinge connector located between the mounting end and the lower end and configured to be pivotably coupled to the actuator link such that the actuator link is located between the lock hinge connector and the piston.

7. The side brace assembly of claim 6 , further comprising a mount, wherein the mounting end of the main body defines a mount hinge connector configured to be pivotably coupled to the mount.

8. The side brace assembly of claim 7 , wherein the lower end of the main body defines a lower hinge connector configured to be pivotably coupled to the lower side brace.

9. The side brace assembly of claim 8 , further comprising the piston configured to be received by the unlock actuator cylinder.

10. The side brace assembly of claim 7 , further comprising lock links extending from the lock hinge connector to the lower side brace.

11. The side brace assembly of claim 7 , further comprising at least one spring, wherein the main body further comprises a spring aperture configured to be coupled to the at least one spring.

12. A landing gear assembly, comprising:
a main fitting configured to support the landing gear assembly;
a retraction actuator configured to retract the landing gear assembly; and
a side brace assembly having:
an actuator link;
a lower side brace, and
an upper side brace having a main body with a mounting end configured to be proximal to an aircraft and a lower end configured to be coupled to the lower side brace, and an unlock actuator cylinder formed monolithic with the main body and configured to house a piston to form an unlock actuator, wherein:
the main body defines fluid channels in fluidic communication with the unlock actuator cylinder and configured to port fluid at least one of to or from the unlock actuator cylinder, and
the main body further defines a lock hinge connector located between the mounting end and the lower end and configured to be pivotably coupled to the actuator link such that the actuator link is located between the lock hinge connector and the piston.

13. The landing gear assembly of claim 12 , further comprising a mount, wherein the mounting end of the main body defines a mount hinge connector configured to be pivotably coupled to the mount.

14. The landing gear assembly of claim 13 , wherein the lower end of the main body defines a lower hinge connector configured to be pivotably coupled to the lower side brace.

15. The landing gear assembly of claim 14 , further comprising the piston configured to be received by the unlock actuator cylinder.

16. The landing gear assembly of claim 12 , further comprising lock links extending from the lock hinge connector to the lower side brace.

17. The landing gear assembly of claim 16 , further comprising at least one spring, wherein the main body further comprises a spring aperture configured to be coupled to the at least one spring.

Assignees

• Goodrich Corp

Inventors

• Goldring Eric
• Ganis Rony Giovanni

Classifications

• B64C25/26 Primary

  Control or locking systems therefor · CPC title

• B64C25/10

  retractable, foldable, or the like · CPC title

• B64C25/22

  fluid · CPC title

• B64C25/34

  wheeled type, e.g. multi-wheeled bogies · CPC title

• B64C25/20

  mechanical · CPC title