Aircraft landing gear

Patent metadata

Field	Value
Publication number	US-9650128-B2
Application number	US-201514599705-A
Country	US
Kind code	B2
Filing date	Jan 19, 2015
Priority date	Jan 19, 2015
Publication date	May 16, 2017
Grant date	May 16, 2017

Abstract

In some embodiments, an aircraft may include a retractable or extendable landing gear. The landing gear may include a wheel connected to an axle, a strut configured to resist longitudinal compression, and a linear actuator that is partially disposed within an opening of the strut.

First claim

What is claimed is:

1. A landing gear for an aircraft, the landing gear comprising:
a wheel in mechanical communication with an axle forming a wheel assembly;
a strut coupled to the wheel assembly and configured to resist longitudinal compression along a first axis, the strut comprising:
a piston having an opening therein; and
a housing associated with the piston; and

a linear actuator comprising:
a one-piece elongated shaft at least partially disposed within the opening of the piston; and
a motor operable to reposition the strut by rotating the elongated shaft;

wherein the piston and the one-piece elongated shaft are substantially centered on the first axis.

2. The landing gear of claim 1 , wherein the piston comprises an elongated tube, and the opening is oriented such that the first axis passes through the opening.

3. The landing gear of claim 1 , wherein the piston is coupled to the wheel assembly.

4. The landing gear of claim 1 , wherein the opening of the piston allows the elongated shaft to move at least partially through the piston.

5. The landing gear of claim 1 , wherein the elongated shaft comprises a threaded surface, and the linear actuator further comprises a ball nut disposed about the threaded surface and coupled to the strut.

6. The landing gear of claim 1 , wherein the motor rotates the elongated shaft relative to the strut.

7. The landing gear of claim 1 , further comprising a support structure comprising:
a first end configured to pivot relative to a second axis that is substantially perpendicular to the first axis; and
a second end configured to pivot relative to a third axis that is substantially parallel to the second axis.

8. The landing gear of claim 1 , wherein the piston has a second opening that allows the elongated shaft to move completely through the piston.

9. An aircraft comprising:
a body;
a landing gear coupled to the body, the landing gear comprising:
a wheel in mechanical communication with an axle forming a wheel assembly;
a strut coupled to the wheel assembly and configured to resist longitudinal compression along a first axis, the strut comprising:
a piston having an opening therein; and
a housing associated with the piston; and

a linear actuator comprising:
a one-piece elongated shaft at least partially disposed within the opening of the piston; and
a motor operable to reposition the strut by moving rotating the elongated shaft;

wherein the piston and the one-piece elongated shaft are substantially centered on the first axis.

10. The aircraft of claim 9 , wherein the piston comprises an elongated tube, and the opening is oriented such that the first axis passes through the opening.

11. The aircraft of claim 9 , wherein the piston is coupled to the wheel assembly.

12. The aircraft of claim 9 , wherein the opening of the piston allows the elongated shaft to move at least partially through the piston.

13. The aircraft of claim 9 , wherein the elongated shaft comprises a threaded surface, and the linear actuator further comprises a ball nut disposed about the threaded surface and coupled to the strut.

14. The aircraft of claim 9 , wherein the motor rotates the elongated shaft relative to the strut.

15. The aircraft of claim 9 , further comprising a support structure comprising:
a first end configured to pivot relative to a second axis that is substantially perpendicular to the first axis; and
a second end configured to pivot relative to a third axis that is substantially parallel to the second axis.

16. The aircraft of claim 9 , wherein the piston has a second opening that allows the elongated shaft to move completely through the piston.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Fenny Carlos A
• Ross Brent C
• Kell Kevin
• Baines Andrew

Classifications

• B64C25/20 Primary

  mechanical · CPC title

• B64C25/12 Primary

  sideways · CPC title

• B64C25/60

  Oleo legs · CPC title

• B64C25/18

  Operating mechanisms · CPC title