AIRCRAFT WING WITH ELECTROTHERMAL DEICING AND/OR ANTI-ICING DEVICE

• US 20070194179A1
• Filed: 02/14/2005
• Published: 08/23/2007
• Est. Priority Date: 03/03/2004
• Status: Active Grant

• Current Assignee: Goodrich Corporation (Rtx Corporation)
• Original Assignee: Goodrich Corporation (Rtx Corporation)
• Inventors: Giamati, Michael
• Granted Patent: US 7,278,610 B2
• Time in Patent Office: Days
• US Class Current: 244/134.00D
• CPC Class Codes: B64C 9/24 by single flap
• CPC Class Codes: B64D 15/12 by electric heating electric heating elements in general H05B
• CPC Class Codes: B64D 15/14 controlled cyclically along length of surface

Abstract

An aircraft wing (12) comprising a structural member (20) forming the wing'"'"'s leading edge skin, a Kreuger flap (16) which moves relative to the structural member (20) between a stowed position and a deployed position, and an electrothermal device (34) mounted (e.g., internally mounted) to the structural member (20). An aft portion (30) of the structural member (20) is curved inwardly to form a recess (32), and a fore portion (18) of the flap (16) fits within the notch (32) to form a joggle therebetween. The electrothermal device (34) is a deicing and/or anti-icing device which continuously provides heat to the curved aft portion (30) of the structural member (20) during icing conditions so as to prevent deployment-inhibiting ice buildup on the flap (16).

Claims

1. A method of removing ice build-up on a susceptible area of an aircraft;

comprising the steps of;

heating a zone adjacent the susceptible area to partially melt the ice build-up on the susceptible area; and

after a delay, heating a zone fore of the susceptible area to provide warm runback water to the partially melt ice build-up.

2. A method as set forth in claim 1, wherein the heating steps are performed by an electrothermal heater mounted to the aircraft;

3. A method as set forth in claim 2, further including the step of de-activating or not activating another zone of the electrothermal device to provide ice dams causing the warm runback water to runback to the susceptible area.

4. A method as set forth in claim 1, wherein the susceptible area is located on an aircraft wing.

5. A method as set forth in claim 4, wherein the susceptible area includes a flap which moves relative to a structural member of the aircraft wing between a stowed position and a deployed position.

6. An aircraft wing comprising a structural member forming a leading edge skin, a flap which moves relative to the structural member between a stowed position and a deployed position, and an electrothermal device mounted to the structural member;

wherein an aft portion of the structural member is recessed inwardly to form a recess, and a fore portion of the flap fits within the recess;

wherein the electrothermal device provides heat to the recessed aft portion of the structural member during icing conditions;

wherein at least one anti-icing zone is positioned to prevent ice build-up that would impede deployment of the movable flap; and

wherein other deicing zones are positioned are provide warm runback flow to the at least one anti-icing zone.

7. An aircraft wing as set forth in claim 6, wherein a lower aft edge of the structural member of the wing is attached to another structural member of the wing by fasteners, and wherein the fasteners are positioned within the recess and covered by the fore portion of the flap.

8. An aircraft wing as set forth in claim 6, wherein the electrothermal device includes deicing zones, which are intermittently activated during icing conditions to remove accumulated ice from corresponding areas of the structural member.

9. An aircraft wing as set forth in claim 8, wherein the deicing zones include a primary deicing zone which covers a major percentage of the surface area of the structural member, including the apex of the structural member.

10. An aircraft wing as set forth in claim 89, wherein the deicing zones include an upper deicing zone, which covers a surface area of the structural member extending from the primary deicing zone to an adjacent aft edge of the structural member, and wherein the upper deicing zone is positioned and operated so as to prevent runback refreeze on unheated upper aft surfaces of the wing.

13. An aircraft wing as set forth in claim 6, wherein the flap lies flush with, or forms a continuation of, a lower surface of the wing in the stowed position and wherein the flap is pivoted outwardly and forms a continuation of an upper surface of the wing in the deployed position.

14. An aircraft comprising a fuselage and two of the aircraft wings set forth in claim 6.

15. An aircraft as set forth in claim 14, wherein the aircraft wings have a sweep angle of greater than 300.

16. A method of removing ice build-up that would prevent the flap of the aircraft wing of claim 6 from being deployed from its stowed position, said method comprising the steps of:

activating an anti-icing zone of the electrothermal device so that heat is provided to the aft portion of the structural member; and

thereafter activating a zone adjacent to the anti-icing zone to provide warm runback water to the ice build-up.

11. (canceled)

12. (canceled)

17. (canceled)

18. (canceled)

19. (canceled)