Landing gear systems for aircraft employing a cross tube

Patent metadata

Field	Value
Publication number	US-10850834-B2
Application number	US-201715840113-A
Country	US
Kind code	B2
Filing date	Dec 13, 2017
Priority date	Dec 13, 2017
Publication date	Dec 1, 2020
Grant date	Dec 1, 2020

Abstract

A landing gear system for an aircraft includes an aft landing gear fitting coupled to the aircraft and a cross tube rotatably coupled to the aft landing gear fitting. The landing gear system also includes first and second wheel fittings coupled to the first and second ends of the cross tube, respectively, and first and second wheels rotatably coupled to the first and second wheel fittings, respectively.

First claim

What is claimed is:

1. A landing gear system for an aircraft comprising:
an aft landing gear fitting coupled to the aircraft;
a cross tube rotatably coupled to the aft landing gear fitting, the cross tube having first and second ends;
first and second wheel fittings configured to be coupled to the first and second ends of the cross tube, respectively;
first and second wheels rotatably coupled to the first and second wheel fittings, respectively; and
first and second skids configured to be coupled to the first and second ends of the cross tube, the first and second skids interchangeable with the first and second wheel fittings on the ends of the cross tube.

2. The landing gear system as recited in claim 1 wherein the aft landing gear fitting further comprises a pivot axis extending in a fore-aft direction, the cross tube rotatably coupled to the aft landing gear fitting about the pivot axis.

3. The landing gear system as recited in claim 1 wherein the aft landing gear fitting is further adapted to receive a skid gear cross tube, the skid gear cross tube and the cross tube adapted to be interchangeably coupled to the aft landing gear fitting.

4. The landing gear system as recited in claim 1 wherein the cross tube further comprises a noncurved horizontal midsection rotatably coupled to the aft landing gear fitting.

5. The landing gear system as recited in claim 4 wherein the cross tube further comprises first and second transition sections each interposed between the midsection and one of the ends of the cross tube, the first transition section sloping downward from the midsection to the first end of the cross tube, the second transition section sloping downward from the midsection to the second end of the cross tube.

6. The landing gear system as recited in claim 1 wherein the cross tube further comprises a material adapted to flex to absorb shocks caused by ground operations of the aircraft.

7. The landing gear system as recited in claim 1 wherein the cross tube forms a shape adapted to flex to absorb shocks caused by ground operations of the aircraft.

8. The landing gear system as recited in claim 1 wherein the cross tube is rotatably coupled to the aft landing gear fitting about an axis lateral to the aircraft.

9. The landing gear system as recited in claim 8 further comprising:
a retraction actuator coupled to the cross tube, the retraction actuator adapted to rotate the cross tube between an extended position and a retracted position about the lateral axis.

10. The landing gear system as recited in claim 1 wherein the wheels further comprise outward-facing wheels.

11. The landing gear system as recited in claim 1 wherein the wheels further comprise inward-facing wheels.

12. An aircraft comprising:
a fuselage having an underside; and
a landing gear system comprising:
an aft landing gear fitting coupled to the underside of the fuselage;
a cross tube rotatably coupled to the aft landing gear fitting, the cross tube having first and second ends;
first and second wheel fittings configured to be coupled to the first and second ends of the cross tube, respectively;
first and second wheels rotatably coupled to the first and second wheel fittings, respectively; and
first and second skids configured to be coupled to the first and second ends of the cross tube, the first and second skids interchangeable with the first and second wheel fittings on the ends of the cross tube.

13. The aircraft as recited in claim 12 wherein the aft landing gear fitting further comprises:
a bridge coupled to the underside of the fuselage; and
a pivot connection fixedly coupled to the cross tube;
wherein the pivot connection is rotatably coupled to the bridge at a pivot axis to allow the cross tube to pivot relative to the fuselage.

14. The aircraft as recited in claim 13 wherein the bridge further comprises first and second ends coupled to the underside of the fuselage.

15. The aircraft as recited in claim 13 wherein the aft landing gear fitting further comprises a pivot pin coupling the pivot connection to the bridge at the pivot axis.

16. The aircraft as recited in claim 12 further comprising first and second struts each having first and second ends, the first ends of the struts coupled to the fuselage, the second ends of the struts each coupled to one of the wheel fittings.

17. The aircraft as recited in claim 16 wherein the struts each further comprise an inline damper.

18. The aircraft as recited in claim 12 wherein the landing gear system further comprises a braking subsystem adapted to selectively reduce rotation of the wheels.

19. The aircraft as recited in claim 12 wherein the landing gear system further comprises a forward wheel assembly removably coupled to the underside of the fuselage.

Assignees

• Textron Innovations Inc

Inventors

• Duval Sebastien
• Ouellet Marc

Classifications

• B64C2025/325

  specially adapted for helicopters · CPC title

• B64C25/52

  Skis or runners · CPC title

• B64C25/34

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

• B64C25/66 Primary

  Convertible alighting gear; Combinations of different kinds of ground or like engaging elements · CPC title

• B64C25/14 Primary

  fore-and-aft · CPC title