Weight reducing landing gear features

Patent metadata

Field	Value
Publication number	US-9499257-B2
Application number	US-201313919781-A
Country	US
Kind code	B2
Filing date	Jun 17, 2013
Priority date	Jun 17, 2013
Publication date	Nov 22, 2016
Grant date	Nov 22, 2016

Abstract

Aircraft landing gear is provided comprising a trunnion arm having a centering portion and a first stress relieving portion and an outer cylinder coupled to the trunnion arm is disclosed. The first stress relieving portion may relieve stress spreading from the centering portion to the outer cylinder. In addition, the first stress relieving portion may be disposed adjacent the centering portion, and may relieve stress spreading from the centering portion to at least one trunnion arm portion. In various embodiments, the aircraft landing gear disclosed herein may further comprise a cross bolt portion formed in a portion of the trunnion arm and a second stress relieving portion disposed adjacent the cross bolt portion. The second stress relieving portion may relieve stress spreading from the cross bolt portion to at least one trunnion arm portion.

First claim

What is claimed is:

1. An aircraft landing gear system comprising:
a trunnion arm extending along a first axis and having a centering portion and a first stress relieving portion,
wherein the centering portion comprises a first perimeter that defines at least one of a first aperture or a first hole,
wherein the first stress relieving portion comprises a second perimeter that defines at least one of a second aperture or a second hole, with the second perimeter defined by an annular surface;
wherein the centering portion and the first stress relieving portion are formed in a surface of the trunnion arm; and
an outer cylinder extending along a second axis and coupled to the trunnion arm,
wherein the first stress relieving portion is configured to relieve stress spreading from the centering portion to the outer cylinder.

2. The aircraft landing gear of claim 1 , wherein the first stress relieving portion is disposed adjacent the centering portion.

3. The aircraft landing gear of claim 1 , wherein the first stress relieving portion relieves stress spreading from the centering portion to the trunnion arm.

4. The aircraft landing gear of claim 1 , further comprising a cross bolt portion formed in a portion of the trunnion arm and a second stress relieving portion disposed adjacent the cross bolt portion.

5. The aircraft landing gear of claim 4 , wherein the second stress relieving portion relieves stress spreading from the cross bolt portion to the trunnion arm.

6. The aircraft landing gear of claim 1 , further comprising a cross bolt portion formed in a portion of the trunnion arm, and a second stress relieving portion and a third stress relieving portion disposed adjacent to the cross bolt portion.

7. The aircraft landing gear of claim 6 , wherein the second stress relieving portion and the third stress relieving portion relieve stress spreading from the cross bolt portion to the trunnion arm.

8. The aircraft landing gear of claim 1 , wherein the trunnion arm has a curved outer profile.

9. The aircraft landing gear of claim 1 , wherein the trunnion arm has circular outer profile.

10. The aircraft landing gear of claim 1 , wherein the trunnion arm has an elliptical outer profile.

11. The aircraft landing gear of claim 7 , wherein the trunnion arm has a cylindrical inner profile.

12. A trunnion arm for a landing gear comprising:
a centering portion including a first perimeter that defines at least one of a first aperture or a first hole; and
a first stress relieving portion disposed adjacent to the centering portion and comprising at least one of a second aperture or a second hole defined by a second perimeter having an annular shape,
wherein the first stress relieving portion relieves stress spreading from the centering portion to other portions of the landing gear including an outer cylinder.

13. The trunnion arm of claim 12 , wherein the first stress relieving portion is disposed adjacent the centering portion.

14. The trunnion arm of claim 12 , wherein the first stress relieving portion relieves stress spreading from the centering portion to at least one trunnion arm portion.

15. The trunnion arm of claim 12 , further comprising a cross bolt portion formed in a portion of the trunnion arm and a second stress relieving portion disposed adjacent the cross bolt portion.

16. The trunnion arm of claim 15 , wherein the second stress relieving portion relieves stress spreading from the cross bolt portion to at least one trunnion arm portion.

17. The trunnion arm of claim 12 , further comprising a cross bolt portion formed in at least one trunnion arm portion and a second stress relieving portion and a third stress relieving portion disposed adjacent the cross bolt portion.

18. The trunnion arm of claim 17 , wherein the second stress relieving portion and the third stress relieving portion relieve stress spreading from the cross bolt portion to the at least one trunnion arm portion.

19. The trunnion arm of claim 12 , wherein the trunnion arm has a curved outer profile.

Assignees

• Goodrich Corp

Inventors

• Baird Bradley William
• Lamoreaux Travis

Classifications

• B64C25/00

  Alighting gear (air-cushion alighting gear B60V3/08) · CPC title

• B64C25/001

  Devices not provided for in the groups B64C25/02 - B64C25/68 · CPC title

• B64C25/02 Primary

  Undercarriages · CPC title