Single axle, semi-levered landing gear with shortening mechanism

Patent metadata

Field	Value
Publication number	US-11136113-B2
Application number	US-201916418021-A
Country	US
Kind code	B2
Filing date	May 21, 2019
Priority date	Jan 25, 2017
Publication date	Oct 5, 2021
Grant date	Oct 5, 2021

Abstract

A landing gear including a shock strut assembly including an outer cylinder coupled to an airframe, a wheel movably coupled to the outer cylinder so as to reciprocate substantially along a longitudinal axis of the outer cylinder, and a shrink mechanism including a pivot arm pivotally coupled to the shock strut assembly, a drive member coupling the pivot arm to a landing gear retract mechanism, a driven member coupled to the pivot arm, a first shrink link member coupled to the pivot arm by the driven member, and a second shrink link member coupled to the first shrink link member and to the shock strut assembly. Rotation of the pivot arm by the drive member, effects a folding movement between the first shrink link member and the second shrink link member, and the folding movement effects at least a retraction of the wheel relative to the outer cylinder.

First claim

What is claimed is:

1. A landing gear comprising:
a shock strut assembly including an outer cylinder coupled to an airframe of an aircraft about a trunnion axis of rotation;
a wheel movably coupled to the outer cylinder so as to reciprocate substantially along a longitudinal axis of the outer cylinder; and
a shrink mechanism including
a pivot arm pivotally coupled to the shock strut assembly,
a drive member coupling the pivot arm to a landing gear retract mechanism,
a driven member coupled to the pivot arm,
a first shrink link member coupled to the pivot arm by the driven member, and
a second shrink link member coupled to the first shrink link member and to the shock strut assembly, so that rotation of the pivot arm by the drive member, effects a folding movement between the first shrink link member and the second shrink link member, and where the folding movement effects at least a retraction of the wheel relative to the outer cylinder.

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

3. The landing gear of claim 1 , further comprising:
a lever member coupled to the first shrink link member so that the lever member and the first shrink link member rotate with each other in a same direction; and
wherein the driven member drives rotation of the first shrink link member through the lever member and effects extension and retraction of the wheel relative to the outer cylinder substantially along the longitudinal axis of the outer cylinder.

4. The landing gear of claim 1 , wherein:
the first shrink link member includes a first end rotatably coupled to the shock strut assembly 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 wheel relative to the outer cylinder and substantially along the longitudinal axis of the outer cylinder.

5. 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.

6. The landing gear of claim 1 , wherein the outer cylinder includes walls, the first shrink link member and the second shrink link member, in a folded configuration, being at least partially disposed between the walls.

7. The landing gear of claim 1 , wherein the driven member is coupled to the first shrink link member so as to effect, under impetus of the drive member, folding and unfolding of the second shrink link member relative to the first shrink link member.

8. The landing gear of claim 1 , wherein the outer cylinder includes a first end having the trunnion axis of rotation and a second end longitudinally spaced from the first end, the pivot arm being pivotally coupled to the outer cylinder between the first end and the second end.

9. The landing gear of claim 1 , wherein the outer cylinder includes an over-center stop surface configured to couple with the shrink mechanism to effect over-center locking of the first shrink link member and the second shrink link member.

10. An aircraft comprising:
an airframe; and
a landing gear coupled to the frame, the landing gear including
a shock strut assembly including an outer cylinder coupled to the airframe about a trunnion axis of rotation;
a wheel movably coupled to the outer cylinder so as to reciprocate substantially along a longitudinal axis of the outer cylinder; and
a shrink mechanism including
a pivot arm pivotally coupled to the shock strut assembly,
a drive member coupling the pivot arm to a landing gear retract mechanism,
a driven member coupled to the pivot arm,
a first shrink link member coupled to the pivot arm by the driven member, and
a second shrink link member coupled to the first shrink link member and to the shock strut assembly, so that rotation of the pivot arm by the drive member, effects a folding movement between the first shrink link member and the second shrink link member, and where the folding movement effects at least a retraction of the wheel relative to the outer cylinder.

11. The aircraft of claim 10 , wherein:
the pivot arm pivots about a first axis of rotation; and
the first shrink link member pivots about a second axis of rotation that is spaced from the first axis of rotation.

12. The aircraft of claim 10 , further comprising:
a lever member coupled to the first shrink link member so that the lever member and the first shrink link member rotate with each other in a same direction; and
wherein the driven member drives rotation of the first shrink link member through the lever member and effects extension and retraction of the wheel relative to the outer cylinder substantially along the longitudinal axis of the outer cylinder.

13. The aircraft of claim 10 , wherein:
the first shrink link member includes a first end rotatably coupled to the shock strut assembly 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 wheel relative to the outer cylinder and substantially along the longitudinal axis of the outer cylinder.

14. The aircraft of claim 10 , 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.

15. The aircraft of claim 10 , wherein the outer cylinder includes walls, the first shrink link member and the second shrink link member, in a folded configuration, being at least partially disposed between the walls.

16. The aircraft of claim 10 , wherein the driven member is coupled to the first shrink link member so as to effect, under impetus of the drive member, folding and unfolding of the second shrink link member relative to the first shrink link member.

17. The aircraft of claim 10 , wherein the outer cylinder includes a first end having the trunnion axis of rotation and a second end longitudinally spaced from the first end, the pivot arm being pivotally coupled to the outer cylinder between the first end and the second end.

18. The aircraft of claim 10 , wherein the outer cylinder includes an over-center stop surface configured to couple with the shrink mechanism to effect over-center locking of the first shrink link member and the second shrink link member.

Assignees

• Boeing Co

Inventors

• Cottet Justin D
• Mellor Mitchell
• Drake Michael L
• Sonnenburg George

Classifications

• B64C25/58

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

• B64C25/20

  mechanical · CPC title

• B64C2025/125

  into the fuselage, e.g. main landing gear pivotally retracting into or extending out of the fuselage · CPC title

• B64C25/34

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

• B64C25/12 Primary

  sideways · CPC title