Cove lip door slaved to trailing edge control device

Patent metadata

Field	Value
Publication number	US-9580168-B2
Application number	US-201414577873-A
Country	US
Kind code	B2
Filing date	Dec 19, 2014
Priority date	Dec 19, 2014
Publication date	Feb 28, 2017
Grant date	Feb 28, 2017

Abstract

A primary flight control device for an aircraft, such as a flaperon attached to an aircraft wing, utilizes independent yet interactive airgap control systems designed to avoid weight penalties associated with conventionally used cam and track systems. An actuator directly controls movements of the flaperon; the flaperon motion is then used to slave separate movements of secondary flight control devices, such as a flaperon hinge panel and a cove lip door, to various positions of the flaperon for indirect control of aerodynamic air gaps during flight. The use of a bell crank for indirectly slaving the flaperon hinge panel movements to the flaperon avoids conventionally used cam and track systems. Although the cove lip door utilizes a separate linkage system, the bell crank and cove lip door linkage systems work in conjunction to assure desired aerodynamic airflows over the aircraft wing and flaperon structures.

First claim

What is claimed is:

1. An aircraft wing configured to be fixed to and extend from an aircraft fuselage, the wing having a leading edge;
a trailing edge;
a primary control device attached to the trailing edge, a linear actuator in communication with the control device, and an aircraft input controller in communication with the linear actuator, wherein movement of the primary control device is subject to the linear actuator via the input controller;
a bell crank mechanism coupled to a secondary control device, and configured to link movement of the linear actuator indirectly to movement of the secondary control device, and
a moveable aerodynamic cove lip door proximal to the primary control device, the cove lip door separately attached to the trailing edge via a cove lip door hinge coupled to an actuator pivot link, the actuator pivot link also attached to the trailing edge;
wherein movement of the cove lip door is an indirect function of movement of the primary control device.

2. The aircraft wing of claim 1 , wherein the bell crank mechanism is also attached to the trailing edge.

3. The aircraft wing of claim 1 , further comprising the actuator pivot link having first and second ends, the actuator being coupled to the linear actuator pivot link at the first end, and the actuator pivot link pivotally connected to, and translationally fixed to, the trailing edge at the second end, and wherein the bell crank mechanism includes a center link also pivotally connected to, but translationally fixed to, the trailing edge.

4. The aircraft wing of claim 3 , further comprising a cove lip door drive arm, a cove lip door drive link fixed to the drive arm, and the cove lip door hinge connected to the cove lip door, the cove lip door drive arm being secured to the actuator pivot link at a position between the first and second ends of the actuator pivot link, wherein the cove door drive link also has first and second ends, the first end of the cove door drive link being rotatably secured to the cove lip door drive arm, and the second end of the cove door drive link rotatably secured to the cove lip door hinge, and wherein movement of the linear actuator moves the actuator pivot link, causing pivotal movement of the cove lip door relative to the trailing edge.

5. The aircraft wing of claim 4 , wherein the actuator pivot link and the drive arm both rotate relative to the trailing edge about the second end of the actuator pivot link.

6. The aircraft wing of claim 1 , wherein the primary control device is a flaperon.

7. The aircraft wing of claim 1 , further comprising at least two bell crank mechanisms, and wherein the secondary control device is a hinge panel.

8. A cove lip door control mechanism secured to an aircraft wing, the wing having a leading edge and a trailing edge and having a primary control device attached to the trailing edge, and a moveable aerodynamic cove lip door proximal to the primary control device, the cove lip door being separately attached to the trailing edge, wherein the cove lip door control mechanism comprises:
a linear actuator, and an aircraft input controller, wherein movement of the primary control device is subject to the linear actuator via the input controller;
a bell crank mechanism coupled to a secondary control device, and configured to link movement of the linear actuator indirectly to movement of the secondary control device;
a cove lip door hinge on the cove lip door for coupling the cove lip door to an actuator pivot link, the actuator pivot link also attached to the trailing edge;
wherein movement of the cove lip door is an indirect function of movement of the primary control device, wherein movement of the cove lip door is slaved to movement of the primary control device.

9. The cove lip door control mechanism of claim 8 , further comprising the linear actuator pivot link having first and second ends, the actuator being coupled to the actuator pivot link at the first end, and the actuator pivot link pivotally connected to, and translationally fixed to, the trailing edge at the second end, and wherein the bell crank mechanism includes a center link pivotally connected to, but translationally fixed to, the trailing edge.

10. The cove lip door control mechanism of claim 9 , further comprising a cove lip door drive arm, a cove lip door drive link, and the cove lip door hinge, the cove lip door drive arm being secured to the actuator pivot link at a position between the first and second ends of the actuator pivot link, wherein the cove door drive link also has first and second ends, the first end of the cove door drive link being rotatably secured to the cove lip door drive arm, and the second end of the cove door drive link rotatably secured to the cove lip door hinge, and wherein movement of the linear actuator moves the actuator pivot link, causing pivotal movement of the cove lip door relative to the trailing edge.

11. The cove lip door control mechanism of claim 10 , wherein the actuator pivot link and the drive arm both rotate relative to the trailing edge about the second end of the actuator pivot link.

12. The cove lip door control mechanism of claim 11 , further comprising at least two bell crank mechanisms, and wherein the secondary control device is a hinge panel.

13. The cove lip door control mechanism of claim 11 , wherein the actuator pivot link and the center link of the bell crank mechanism are spaced apart.

14. The cove lip door control mechanism of claim 8 , wherein the cove lip door control mechanism is configured to impart reciprocal motion to the actuator pivot link.

15. The cove lip door control mechanism of claim 14 , wherein the primary control device is a flaperon.

16. A method of slaving motion of an aircraft cove lip door to movement of a primary flight control device, the method comprising the steps of:
providing a cove lip door control mechanism for an aircraft wing, the wing configured to be fixed to and extend from an aircraft fuselage, the wing having a leading edge and a trailing edge;
providing a primary control device and attaching the primary control device to the trailing edge;
providing a linear actuator configured to operate the primary control device;
providing an aircraft input controller configured to move the linear actuator, wherein movement of the primary control device is subject to the linear actuator via the input controller;
providing a bell crank mechanism coupled to a secondary control device, and configured to link movement of the linear actuator directly to movement of the secondary control device;
providing a cove lip door having a hinge, the hinge coupled to an actuator pivot link, and attaching the actuator pivot link to the trailing edge;
providing a moveable aerodynamic cove lip door proximal to the primary control device, the cove lip door separately attached to the trailing edge; and
configuring movement of the cove lip door to be an indirect function of movement of the primary control device.

17. The method of claim 16 , including a further step of providing the actuator pivot link configured to be directly slaved to movement of the primary control device.

Assignees

• Boeing Co

Inventors

• Fevergeon Matthew D M
• Kordel Jan A
• Liu Victor

Classifications

• B64C9/18

  by single flaps · CPC title

• B64C9/10

  one surface adjusted by movement of another, e.g. servo tabs (B64C9/04 takes precedence; adjusting surfaces of different type or function B64C9/12) · CPC title

• B64C3/50

  by leading or trailing edge flaps · CPC title

• B64C9/04 Primary

  with compound dependent movements · CPC title

• B64C3/28 Primary

  Leading or trailing edges attached to primary structures, e.g. forming fixed slots · CPC title