Undercarriage-mounted airfoil

Patent metadata

Field	Value
Publication number	US-10589840-B2
Application number	US-201715435959-A
Country	US
Kind code	B2
Filing date	Feb 17, 2017
Priority date	Feb 17, 2017
Publication date	Mar 17, 2020
Grant date	Mar 17, 2020

Abstract

An aircraft nose gear-mounted flight control device promotes aircraft stability during low-speed phases of flight, including take-offs and landings. The flight control device is an operable airfoil secured to an aircraft nose gear, either to a vertical support strut or to a wheel axle thereof. The airfoil is deployed when the nose gear is deployed, and is retracted when the nose gear is retracted. Upon deployment, the airfoil is effective to at least provide aircraft pitch control. In some configurations, the airfoil deploys as two separate but mirror-imaged left and right airfoil components that move in concert to provide pitch control. In other configurations, the airfoil components move at relatively different angular rates and amounts to provide both pitch and roll control. The entire airfoil may be pivotal for pitch control, or may instead be fixed, but have moveable flaps or flap-like portions that provide pitch control.

First claim

What is claimed is:

1. A flight control device for an aircraft, the aircraft including an undercarriage; the flight control device comprising:
an airfoil retractably mounted to the undercarriage, wherein the airfoil is extensible from the undercarriage, and includes a first coupling joint for pivotably securing an inboard extremity of the airfoil to the undercarriage, a second coupling joint on the airfoil spaced outboard of the first coupling joint, and a support linkage that pivotally secures the second coupling joint to the undercarriage, wherein the airfoil pivots about the first coupling joint upon extension of the airfoil from the undercarriage.

2. The flight control device of claim 1 , wherein the airfoil has a trailing edge flap.

3. The flight control device of claim 1 , wherein the airfoil includes a vertically oriented outboard element to provide lateral directional stability control.

4. The flight control device of claim 1 , wherein the airfoil is cambered.

5. The flight control device of claim 1 , further comprising a retractable landing gear extensible from the undercarriage, wherein the airfoil is mounted to the retractable landing gear for deployment with the retractable landing gear during low-speed flight.

6. The flight control device of claim 5 , wherein the landing gear is a nose gear.

7. The flight control device of claim 6 , wherein the airfoil is deployed when the nose gear is deployed; wherein the airfoil is retracted when the nose gear is retracted; and wherein when deployed the airfoil provides aircraft pitch control.

8. The flight control device of claim 6 , wherein the airfoil comprises at least two airfoil components, and the airfoil components are configured for aircraft pitch and roll movements.

9. The flight control device of claim 8 , wherein the at least two airfoil components are left and right airfoil components configured to move differentially about a roll axis of the aircraft, each airfoil component being relatively movable with respect to the other at different angular rates and amounts.

10. The flight control device of claim 6 , wherein the airfoil comprises at least two airfoil components, and the airfoil components are configured for pitch control movements.

11. The flight control device of claim 10 , wherein the nose gear includes a vertical support strut, and further includes a pair of support and companion linkages attached to the vertical support strut; wherein the support and companion linkages are also attached to the airfoil components; and wherein the airfoil components are configured for deployment by telescoping movement of the linkages.

12. The flight control device of claim 10 , wherein the deployed airfoil components comprise a positive dihedral angle.

13. The flight control device of claim 10 , wherein the deployed airfoil components comprise a negative dihedral angle.

14. An aircraft having a retractable gear, and a flight control device mounted on the gear; the flight control device comprising:
an airfoil operably secured to the gear;
wherein the airfoil is deployed when the gear is deployed; and
wherein the airfoil is retracted when the gear is retracted; and
wherein, the airfoil includes a first coupling joint for pivotably securing an inboard extremity thereof to the retractable gear, a second coupling joint on the airfoil spaced outboard of the first coupling joint, and a support linkage that pivotally secures the second coupling joint to the retractable gear, wherein the airfoil pivots about the first coupling joint upon deployment from the retractable gear.

15. The aircraft of claim 14 , wherein the airfoil is mounted on an axle of the gear.

16. The aircraft of claim 14 , wherein the airfoil is configured to control pitch of the aircraft.

17. The aircraft of claim 14 , wherein the airfoil is configured to control pitch and roll of the aircraft.

18. The aircraft of claim 14 , wherein the airfoil comprises at least left and right airfoil components; wherein the gear includes a vertical support strut having a pair of support and companion linkages attached to the vertical support strut; wherein the support and companion linkages are also attached to the left and right airfoil components; and wherein the airfoil components are configured for deployment by telescoping movement of the linkages.

19. The aircraft of claim 18 , wherein the left and right airfoil components are configured to move differentially about a roll axis of the aircraft, each airfoil component being relatively movable with respect to the other at different angular rates and amounts.

20. A method of enhancing control of an aircraft during low-speed flight; the method comprising steps of:
forming an airfoil having a first coupling joint for pivotably securing an inboard extremity thereof to a retractable gear of an aircraft, a second coupling joint on the airfoil spaced outboard of the first coupling joint, and a support linkage that pivotably secures the second coupling joint to the retractable gear;
configuring the airfoil to deploy when the gear is deployed, wherein upon deployment of the retractable gear the airfoil pivots about the first coupling joint;
affixing the airfoil to the retractable gear;
configuring the airfoil to retract when the gear is retracted; and
configuring the airfoil to be moveable during flight to actively control the airplane when deployed.

Assignees

• Boeing Co

Inventors

• Brown John Joseph
• Harrison Neal A

Classifications

• B64C25/16

  Fairings movable in conjunction with undercarriage elements · CPC title

• B64C9/26

  by multiple flaps · CPC title

• B64C9/02

  Mounting or supporting thereof · CPC title

• B64C9/36 Primary

  the members being fuselages or nacelles · CPC title

• B64C9/16

  at the rear of the wing · CPC title