Slotted flaperon seal mechanism for aircraft devices

Patent metadata

Field	Value
Publication number	US-11046421-B2
Application number	US-201816164033-A
Country	US
Kind code	B2
Filing date	Oct 18, 2018
Priority date	Oct 18, 2018
Publication date	Jun 29, 2021
Grant date	Jun 29, 2021

Abstract

One embodiment is an apparatus comprising an aircraft wing; a control surface hingedly connected to a trailing edge of the aircraft wing, wherein a slot is provided between the aircraft wing and the control surface; a seal disposed over the slot, the seal hingedly connected to the aircraft wing; a spring mechanism for preloading the seal against a surface of the control surface such that the gap is sealed with the control surface is in a first position relative to the aircraft wing; and at least one cam blade for lifting the seal from the surface of the control surface as the control surface moves from the first position to a second position relative to the aircraft wing and returning the seal to the surface of the control surface as the control surface moves from the second position to the first position.

First claim

What is claimed is:

1. An apparatus comprising: an aircraft wing;
a control surface hingedly connected to a trailing edge of the aircraft wing, wherein an aerodynamic slot is provided between the aircraft wing and the control surface;
a seal disposed over the aerodynamic slot, the seal having a hinged connection to the aircraft wing;
a spring mechanism for preloading the seal against a surface of the control surface such that a gap is sealed with the control surface is in a first position relative to the aircraft wing; and
at least one cam blade for lifting the seal from the surface of the control surface as the control surface moves from the first position to a second position relative to the aircraft wing and returning the seal to the surface of the control surface as the control surface moves from the second position to the first position;
wherein the first position corresponds to a negative flap angle and the second position corresponds to a first positive flap angle; and
wherein the cam blade is configured such that the seal is returned directly to the surface of the control surface by the spring mechanism as the control surface moves from the second position to a third position relative to the aircraft wing, wherein the third position corresponds to a maximum positive flap angle greater than the first positive flap angle.

2. The apparatus of claim 1 further comprising an actuator for moving the control surface relative to the aircraft wing.

3. The apparatus of claim 1 , wherein the at least one cam blade is disposed on the surface of the control surface.

4. The apparatus of claim 1 , wherein the at least one cam blade comprises a plurality of cam blades disposed along a length of a leading edge of the control surface for enabling airflow through a plurality of gaps created by the cam blades between the seal and the control surface.

5. The apparatus of claim 1 , wherein the spring mechanism comprises at least one of a linear spring and a torsional spring.

6. The apparatus of claim 1 , wherein the control surface comprises a flaperon.

7. A rotorcraft comprising: an aircraft wing;
a control surface hingedly connected to a trailing edge of the aircraft wing, wherein an aerodynamic slot is provided between the aircraft wing and the control surface;
a seal disposed over the aerodynamic slot, the seal having a hinged connection to the aircraft wing;
a spring mechanism for preloading the seal against a surface of the control surface such that a gap is sealed with the control surface is in a first position relative to the aircraft wing; and
at least one cam blade for lifting the seal from the surface of the control surface as the control surface moves from the first position to a second position relative to the aircraft wing and returning the seal to the surface of the control surface as the control surface moves from the second position to the first position;
wherein the first position corresponds to a negative flap angle and the second position corresponds to a first positive flap angle; and
wherein the cam blade is configured such that the seal is returned directly to the surface of the control surface by the spring mechanism as the control surface moves from the second position to a third position relative to the aircraft wing, wherein the third position corresponds to a maximum positive flap angle greater than the first positive flap angle.

8. The rotorcraft of claim 7 further comprising an actuator for moving the control surface relative to the aircraft wing.

9. The rotorcraft of claim 7 , wherein the at least one cam blade is disposed on the surface of the control surface.

10. The rotorcraft of claim 7 , wherein the at least one cam blade comprises a plurality of cam blades disposed along a length of a leading edge of the control surface for enabling airflow through a plurality of gaps created by the cam blades between the seal and the control surface.

11. The rotorcraft of claim 7 , wherein the spring mechanism comprises at least one of a linear spring and a torsional spring.

12. The rotorcraft of claim 7 , wherein the control surface comprises a flaperon.

13. An aircraft wing comprising:
a control surface hingedly connected to a trailing edge of the aircraft wing, wherein an aerodynamic slot is provided between the aircraft wing and the control surface;
a seal disposed over the aerodynamic slot, the seal having a hinged connection to the aircraft wing;
a spring mechanism for preloading the seal against a surface of the control surface such that a gap is sealed with the control surface is in a first position relative to the aircraft wing; and
at least one cam blade for lifting the seal from the surface of the control surface as the control surface moves from the first position to a second position relative to the aircraft wing and returning the seal to the surface of the control surface as the control surface moves from the second position to the first position;
wherein the first position corresponds to a negative flap angle and the second position corresponds to a first positive flap angle; and
wherein the cam blade is configured such that the seal is returned directly to the surface of the control surface by the spring mechanism as the control surface moves from the second position to a third position relative to the aircraft wing, wherein the third position corresponds to a maximum positive flap angle greater than the first positive flap angle.

14. The aircraft wing of claim 13 , wherein the at least one cam blade comprises a plurality of cam blades disposed along a length of a leading edge of the control surface for enabling airflow through a plurality of gaps created by the cam blades between the seal and the control surface.

15. The aircraft wing of claim 13 , wherein the spring mechanism comprises at least one of a linear spring and a torsional spring.

Assignees

• Bell Helicopter Textron Inc
• Textron Innovations Inc

Inventors

• Decker George R
• Robedeau Jr Steven Allen

Classifications

• B64C9/02 Primary

  Mounting or supporting thereof · CPC title

• B64C7/00

  Structures or fairings not otherwise provided for · CPC title

• Y02T50/30

  Wing lift efficiency · CPC title

• B64C27/04

  Helicopters · CPC title

• B64C29/0033

  the propellers being tiltable relative to the fuselage · CPC title