Landing gear shrink link mechanism

Patent metadata

Field	Value
Publication number	US-10981646-B2
Application number	US-201816049090-A
Country	US
Kind code	B2
Filing date	Jul 30, 2018
Priority date	Jul 30, 2018
Publication date	Apr 20, 2021
Grant date	Apr 20, 2021

Abstract

A landing gear including an outer cylinder rotatably coupled to a frame of an aircraft about a trunnion axis of rotation, a shock strut assembly movably coupled to the outer cylinder so as to reciprocate along a longitudinal axis of the outer cylinder, and a shrink mechanism including a first shrink link member pivotally coupled to the outer cylinder, a second shrink link member coupling the first shrink link member to the shock strut assembly, a crank member pivotally coupled to the outer cylinder, a drive member coupling the crank member to a walking beam (a.k.a. retract actuator beam) of a landing gear retract mechanism, and a driven member coupling the crank member to the first shrink link member.

First claim

What is claimed is:

1. A landing gear comprising:
an outer cylinder rotatably coupled to a frame of an aircraft about a trunnion axis of rotation;
a shock strut assembly movably coupled to the outer cylinder so as to reciprocate along a longitudinal axis of the outer cylinder; and
a shrink mechanism including
a first shrink link member pivotally coupled to the outer cylinder,
a second shrink link member coupling the first shrink link member to the shock strut assembly,
a crank member pivotally coupled to the outer cylinder,
a drive member coupling the crank member to a walking beam of a landing gear retract mechanism, and
a driven member coupling the crank member to the first shrink link member.

2. The landing gear of claim 1 , wherein:
the crank member pivots about a first axis of rotation; and
the first shrink link member pivots about a second axis of rotation that is spaced, along the longitudinal axis of the outer cylinder, from the first axis of rotation.

3. The landing gear of claim 1 , further comprising:
a shrink crank member coupled to the first shrink link member so that the shrink crank member and the first shrink link member rotate as a unit; and
wherein the driven member is coupled to the shrink crank member so as to drive rotation of the first shrink link member and effect extension and retraction of the shock strut assembly relative to the outer cylinder and along the longitudinal axis.

4. The landing gear of claim 3 , wherein the first shrink link member includes a first end rotatably coupled to the outer cylinder and a second end rotatably coupled to the second shrink link member, the shrink crank member being disposed adjacent the first end of the first shrink link member.

5. The landing gear of claim 3 , wherein the first shrink link member includes a crank member receiver configured to receive the shrink crank member so that the shrink crank member is rotationally fixed relative to the first shrink link member.

6. The landing gear of claim 1 , wherein:
the first shrink link member includes a first end rotatably coupled to the outer cylinder and a second end rotatably coupled to the second shrink link member; and
the driven member is pivotally coupled to the first shrink link member adjacent the second end so as to drive rotation of the first shrink link member and effect extension or retraction of the shock strut assembly relative to the outer cylinder and along the longitudinal axis.

7. The landing gear of claim 1 , wherein the first shrink link member and the second shrink link member are rotatably coupled to each other so as to fold and unfold relative to each other and lock in an over-center position when unfolded.

8. An aircraft comprising:
a frame; and
a landing gear coupled to the frame, the landing gear including
an outer cylinder rotatably coupled to a frame of the aircraft about a trunnion axis of rotation;
a shock strut assembly movably coupled to the outer cylinder so as to reciprocate along a longitudinal axis of the outer cylinder; and
a shrink mechanism including
a first shrink link member pivotally coupled to the outer cylinder,
a second shrink link member coupling the first shrink link member to the shock strut assembly,
a crank member pivotally coupled to the outer cylinder,
a drive member coupling the crank member to a walking beam of a landing gear retract mechanism, and
a driven member coupling the crank member to the first shrink link member.

9. The aircraft of claim 8 , further comprising:
a sensor actuator arm coupled to the first shrink link member so as to rotate with the first shrink link member; and
a sensor coupled to the outer cylinder;
wherein the sensor is configured to sense the sensor actuator arm upon extension of the shock strut assembly.

10. The aircraft of claim 8 , wherein the outer cylinder includes a shrink link cavity and the first shrink link member and the second shrink link member are disposed within the shrink link cavity and are enclosed by the outer cylinder.

11. The aircraft of claim 10 , wherein the outer cylinder includes a cover configured to enclose the first shrink link member and the second shrink link member within the shrink link cavity.

12. The aircraft of claim 10 , wherein the shrink link cavity includes a fluid drainage aperture.

13. The aircraft of claim 8 , further comprising:
a door pivotally coupled to the frame about a door pivot axis; and
a door drive member coupling the door to the outer cylinder so that rotation of the outer cylinder about the trunnion axis of rotation effects pivoting of the door about the door pivot axis.

14. The aircraft of claim 8 , wherein the outer cylinder includes an inner cavity and the shock strut assembly comprises:
a bulkhead movably coupled to the inner cavity so as to form a first seal with the inner cavity, the bulkhead being coupled to the shrink mechanism; and
an inner cylinder movably coupled to both the inner cavity and the bulkhead so as to form a second seal with the inner cavity and so that the inner cylinder is movable with the bulkhead relative to the outer cylinder;
wherein the shrink mechanism effects relative movement of both the bulkhead and the inner cylinder so as to one of increase or decrease a length of the landing gear depending on a respective deployed or retracted configuration of the landing gear.

15. A method of operating a landing gear of an aircraft, the method comprising:
rotating the landing gear about a trunnion axis of rotation, where the trunnion axis of rotation is defined by an outer cylinder of the landing gear; and
moving a shock strut assembly relative to the outer cylinder with a shrink link mechanism, where the outer cylinder at least partially surrounds the shock strut assembly and the shrink link mechanism includes:
a first shrink link member pivotally coupled to the outer cylinder,
a second shrink link member coupling the first shrink link member to the shock strut assembly,
a crank member pivotally coupled to the outer cylinder,
a drive member coupling the crank member to a walking beam of a landing gear retract mechanism, and
a driven member coupling the crank member to the first shrink link member.

16. The method of claim 15 , further comprising:
pivoting the crank member about a first axis of rotation; and
pivoting the first shrink link member about a second axis of rotation that is spaced from the first axis of rotation along a longitudinal axis of the outer cylinder;
wherein the first axis of rotation and the second axis of rotation are substantially parallel with one another.

17. The method of claim 15 , further comprising:
pivoting the crank member about a first axis of rotation; and
pivoting the first shrink link member about a second axis of rotation that is spaced from the first axis of rotation along a longitudinal axis of the outer cylinder;
wherein the drive member and the driven member extend substantially along the longitudinal axis adjacent one another.

18. The method of claim 15 , further comprising:
pivoting the crank member about a first axis of rotation; and
pivoting the first shrink link member about a second axis of rotation that is spaced from the first axis of rotation along a longitudinal axis of the outer cylinder;
wherein the first axis of rotation and the second axis of rotation cross one another.

19. The method of claim 15 , further comprising folding and unfolding of the second shrink link member relative to the first shrink link member with the driven member under im

Assignees

• Boeing Co

Inventors

• Alley Christopher M
• Campbell Leanne M
• Defrancisci Gabriela K
• Vering Gregory J
• Knock Aaron P
• Mellor Mitchell
• Cottet Justin D

Classifications

• B64C25/60

  Oleo legs · CPC title

• B64C25/12 Primary

  sideways · CPC title

• B64C25/20 Primary

  mechanical · CPC title

• B64C25/34

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

• B64C25/58

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