Chock for steering mechanism of an aircraft nose landing gear

Patent metadata

Field	Value
Publication number	US-12466581-B2
Application number	US-202318313571-A
Country	US
Kind code	B2
Filing date	May 8, 2023
Priority date	May 8, 2023
Publication date	Nov 11, 2025
Grant date	Nov 11, 2025

Abstract

A device to engage with a steering mechanism of a nose landing gear of an aircraft to limit steering rotation of the nose landing gear. The device includes a first chock sized to fit within a first space formed in the nose landing gear at a first cylinder of a steering mechanism, and a second chock sized to fit within a second space formed in the nose landing gear at a second cylinder. The first chock is configured to engage with the first cylinder and to compress to prevent retraction of the first cylinder beyond a first predetermined length. The second chock is configured to engage with the second cylinder and to compress to prevent retraction of the second cylinder beyond a second predetermined length.

First claim

What is claimed is:

1 . A device to engage with a steering mechanism of a nose landing gear of an aircraft to limit steering rotation of the nose landing gear, the device comprising:
a first chock sized to fit within a first space formed in the nose landing gear at a first cylinder of a steering mechanism of the nose landing gear; a second chock sized to fit within a second space formed in the nose landing gear at a second cylinder of the steering mechanism; wherein the first chock is configured to engage with the first cylinder and to compress to prevent retraction of the first cylinder beyond a first predetermined length; and wherein the second chock is configured to engage with the second cylinder and to compress to prevent retraction of the second cylinder beyond a second predetermined length.

2 . The device of claim 1 , wherein the first chock and the second chock are separate members that configured to be spaced apart by a gap when engaged respectively with the first cylinder and the second cylinder.

3 . The device of claim 2 , further comprising an elongated flexible connector with a first end connected to the first chock and a second end connected to the second chock.

4 . The device of claim 2 , wherein the first chock and the second chock comprise mirrored shapes.

5 . The device of claim 1 , wherein the first chock and the second chock comprise a single, unitary member with the member comprising an intermediate section sized to extend across a gap formed between the first cylinder and the second cylinder.

6 . A device to engage with a steering mechanism of a nose landing gear of an aircraft to limit steering rotation of the nose landing gear, the device comprising:
a first chock sized to fit within a first space at a first section of a steering mechanism of the nose landing gear; a second chock sized to fit within a second space at a second section of the steering mechanism of the nose landing gear; the first chock and the second chock each comprising:
a front contact side;
a back contact side that opposes the front contact side;
a bottom side;
a top side that opposes the bottom side;
wherein the first chock is sized to fit within the first space and to compress when the steering mechanism turns the nose landing gear in a first direction; and wherein the second chock is sized to fit within the second space and to compress when the steering mechanism turns the nose landing gear in a second direction.

7 . The device of claim 6 , wherein the first chock and the second chock are separate members.

8 . The device of claim 7 , further comprising an elongated flexible connector with a first end connected to the first chock and a second end connected to the second chock.

9 . The device of claim 8 , wherein the first chock and the second chock comprise a single, unitary member with the member comprising an intermediate section sized to extend across a gap formed between the first section and the second section of the steering mechanism.

10 . The device of claim 6 , wherein the first chock comprises a central slot that extends through the first chock between the front contact side and the back contact side, the first chock further comprising an opening that extends into the central slot along a lateral side of the first chock.

11 . A method of limiting steering rotation of a nose landing gear of an aircraft, the method comprising:
inserting a first chock in a first space formed between a first cylinder and the nose landing gear; inserting a second chock in a second space formed between a second cylinder and the nose landing gear; wherein the first chock is configured to compress and limit steering rotation of the nose landing gear in a first direction; and wherein the second chock is configured to compress and limit the steering rotation of the nose landing gear in a second direction.

12 . The method of claim 11 , further comprising:
turning the nose landing gear in the first direction and compressing the first chock and limiting the steering rotation of the nose landing gear in the first direction; and turning the nose landing gear in the second direction and compressing the second chock and limiting the steering rotation of the nose landing gear in the second direction.

13 . The method of claim 12 , further comprising maintaining the first chock connected with a connector to the second chock while turning the nose landing gear in the first direction and the second direction.

14 . The method of claim 12 , further comprising turning the nose landing gear in the first direction and increasing a size of the second space while concurrently compressing the first chock.

15 . The method of claim 12 , further comprising inserting the first chock underneath a first arm that extends outward from the first cylinder and inserting the second chock underneath a second arm that extends outward from the second cylinder.

16 . The method of claim 12 , further comprising:
in response to turning the nose landing gear in the first direction, compressing the first chock and preventing a steering angle of the nose landing gear from turning beyond a first predetermined amount in the first direction; and in response to turning the nose landing gear in the second direction, compressing the second chock and preventing the steering angle of the nose landing gear from turning beyond a second predetermined amount in the second direction.

17 . The method of claim 11 , further comprising attaching the first chock to a first arm that extends outward from the first cylinder and attaching the second chock to a second arm that extends outward from the second cylinder.

18 . The method of claim 12 , further comprising spacing the first chock away from the second chock.

19 . The method of claim 12 , further comprising the first chock and the second chock being a single unitary member and compressing the first chock when turning the nose landing gear in the first direction without compressing an intermediate section that extends between the first chock and the second chock and turning the nose landing gear in the second direction without compressing the intermediate section.

20 . The method of claim 12 , further comprising inserting the first chock in the first space and the second chock in the second space when the nose landing gear is at a 0 steering angle.

Assignees

• Boeing Co

Inventors

• Toon Nicholas
• Bakken Lance Joseph
• Adams Andrew Henry
• Harr Brian A

Classifications

• B64C25/50

  Steerable undercarriages; Shimmy-damping · CPC title

• B64F1/16 Primary

  Pickets or ground anchors; Wheel chocks · CPC title