Composite landing gear apparatus and methods

• US 20060284009A1
• Filed: 06/03/2005
• Published: 12/21/2006
• Est. Priority Date: 06/03/2005
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Kismarton, Max U.
• Granted Patent: US 7,467,763 B2
• Time in Patent Office: Days
• US Class Current: 244/104.LS
• CPC Class Codes: B64C 2025/325 specially adapted for helicopters
• CPC Class Codes: B64C 25/10 retractable, foldable, or the like

Abstract

Composite landing gear apparatus and methods are disclosed. In one embodiment, a composite component includes an elongated member having a first composite portion coupled to a second composite portion by a pair of composite sidewall portions and forming an elongated cavity therebetween. The first composite portion includes a plurality of first layers, each first layer having a plurality of first fibers disposed therein. Similarly, the second composite portion includes a plurality of second layers, each second layer having a plurality of second fibers disposed therein. The first and second fibers are oriented substantially parallel to a longitudinal axis of the elongated cavity. The composite sidewall portions include a plurality of third layers each third layer having a plurality of third fibers disposed therein, the third fibers being cross-woven and non-parallel with the longitudinal axis.

Claims

1. A composite component, comprising:

an elongated member having a first composite portion coupled to a second composite portion by a pair of composite sidewall portions and forming an elongated cavity therebetween, wherein the first composite portion includes a plurality of first layers, each first layer having a plurality of first fibers disposed therein, and wherein the second composite portion includes a plurality of second layers, each second layer having a plurality of second fibers disposed therein, wherein the first and second fibers are oriented substantially parallel to a longitudinal axis of the elongated cavity, and wherein the composite sidewall portions include a plurality of third layers, each third layer having a plurality of third fibers disposed therein, the third fibers being cross-woven and non-parallel with the longitudinal axis.

2. The component of claim 1, wherein the elongated member comprises a square-shaped elongated member.

3. The component of claim 1, wherein the first fibers have a greater strain of compression than the second fibers, and the second fibers have a greater strain of tension than the first fibers.

4. The component of claim 3, wherein the third fibers have a lower strain of compression than at least one of the first and second fibers and a lower strain of tension than at least one of the first and second fibers.

5. The component of claim 1, wherein the first fibers include glass fibers and the second fibers include plastic fibers.

6. The component of claim 5, wherein the third fibers include carbon fibers.

7. A landing gear assembly for an aircraft, comprising:

a receiving member adapted to be coupled to a frame member of the aircraft, the receiving member including a receiving portion defining a receptacle; and

an elongated member having a first end disposed within and coupled to the receptacle and a second end operatively coupled to a landing member, the elongated member further having a first composite portion coupled to a second composite portion by a pair of composite sidewall portions and forming an elongated cavity therebetween, wherein the first composite portion includes a plurality of first layers, each first layer having a plurality of first fibers disposed therein, and wherein the second composite portion includes a plurality of second layers, each second layer having a plurality of second fibers disposed therein, wherein the first and second fibers are oriented substantially parallel to a longitudinal axis of the elongated cavity, and wherein the composite sidewall portions include a plurality of third layers, each third layer having a plurality of third fibers disposed therein, the third fibers being cross-woven and non-parallel with the longitudinal axis.

8. The assembly of claim 7, wherein the receiving portion includes a wall member having at least one aperture disposed therein, the first end of the elongated member being coupled to the receptacle by an attachment member passing through the aperture, the wall member including a structurally-weakened portion proximate the aperture.

9. The assembly of claim 8, wherein the structurally-weakened portion is adapted to structurally fail at a first load level applied to the landing member, and wherein the elongated member is adapted to structurally fail at a second load level applied to the landing member, the first load level being lower than the second load level.

10. The assembly of claim 7, wherein the elongated member comprises a square-shaped elongated member, and wherein the receptacle comprises a square-shaped receptacle.

11. The assembly of claim 7, wherein the first fibers have a greater strain of compression than the second fibers, and the second fibers have a greater strain of tension than the first fibers.

12. The assembly of claim 7, wherein the first fibers include glass fibers, the second fibers include plastic fibers, and the third fibers include carbon fibers.

13. An aircraft, comprising:

a frame assembly;

a fuselage operatively coupled to the frame assembly; and

a landing gear assembly including;

at least one receiving member coupled to the frame assembly, the receiving member including a receiving portion defining a receptacle; and

at least one elongated member having a first end disposed within and coupled to the receptacle and a second end operatively coupled to a landing member, the elongated member further having a first composite portion coupled to a second composite portion by a pair of composite sidewall portions and forming an elongated cavity therebetween, wherein the first composite portion includes a plurality of first layers, each first layer having a plurality of first fibers disposed therein, and wherein the second composite portion includes a plurality of second layers, each second layer having a plurality of second fibers disposed therein, wherein the first and second fibers are oriented substantially parallel to a longitudinal axis of the elongated cavity, and wherein the composite sidewall portions include a plurality of third layers, each third layer having a plurality of third fibers disposed therein, the third fibers being cross-woven and non-parallel with the longitudinal axis.

14. The aircraft of claim 13, wherein the receiving portion includes a wall member having at least one aperture disposed therein, the first end of the elongated member being coupled to the receptacle by an attachment member passing through the aperture, the wall member including a structurally-weakened portion proximate the aperture.

15. The aircraft of claim 14, wherein the structurally-weakened portion is adapted to structurally fail at a first load level applied to the landing member, and wherein the elongated member is adapted to structurally fail at a second load level applied to the landing member, the first load level being lower than the second load level.

16. The aircraft of claim 13, wherein the elongated member comprises a square-shaped elongated member, and wherein the receptacle comprises a square-shaped receptacle.

17. The aircraft of claim 13, wherein the first fibers have a greater strain of compression than the second fibers, and the second fibers have a greater strain of tension than the first fibers.

18. The aircraft of claim 13, wherein the first fibers include glass fibers, the second fibers include plastic fibers, and the third fibers include carbon fibers.

19. A landing gear assembly for an aircraft, comprising:

a receiving member adapted to be coupled to a frame member of the aircraft, the receiving member including a receiving portion defining a receptacle, wherein the receiving portion includes a wall member having at least one aperture disposed therein, the wall member including a structurally-weakened portion proximate the aperture and

an elongated member having a first end disposed within the receptacle and a second end operatively coupled to a landing member, the first end of the elongated member being coupled to the receptacle by an attachment member passing through the aperture, the structurally-weakened portion being adapted to structurally fail at a first load level applied to the landing member, and the elongated member being adapted to structurally fail at a second load level applied to the landing member, the first load level being lower than the second load level.

20. The assembly of claim 19, wherein the elongated member further includes a first composite portion coupled to a second composite portion by a pair of sidewall portions and forming an elongated cavity therebetween, wherein the first composite portion includes a plurality of first layers, each first layer having a plurality of first fibers disposed therein, and wherein the second composite portion includes a plurality of second layers, each second layer having a plurality of second fibers disposed therein, wherein the first and second fibers are oriented substantially parallel to a longitudinal axis of the elongated cavity, and wherein the sidewall portions include a plurality of third layers, each third layer having a plurality of third fibers disposed therein, the third fibers being cross-woven and non-parallel with the longitudinal axis.