Modular anti-icing/de-icing device for an aerodynamic surface

• US 20050184193A1
• Filed: 12/10/2004
• Published: 08/25/2005
• Est. Priority Date: 12/12/2003
• Status: Active Grant

• Current Assignee: Airbus Helicopters
• Original Assignee: Eurocopter
• Inventors: Cuadrado, Gerard, Bourjac, Didier
• Granted Patent: US 7,523,889 B2
• Time in Patent Office: Days
• US Class Current: 244/10
• CPC Class Codes: B64C 27/04 Helicopters
• CPC Class Codes: B64D 15/12 by electric heating electric heating elements in general H05B
• CPC Class Codes: B64D 15/22 Automatic initiation by icing detector

Abstract

A anti-icing/de-icing device for an aircraft wing includes at least one aerodynamic surface, e.g. a rotorcraft blade or an airplane wing, the aerodynamic surface possessing at least two anti-icing/de-icing modules 17, with each module 17 being provided with a respective heater element 54. In addition, the heater elements 54 of the modules 17 are powered electrically by a common electrical power supply member 1, each anti-icing/de-icing module acting against icing in its own zone independently of the other module(s).

Claims

1. An anti-icing/de-icing device for an aircraft wing, said wing including at least one first aerodynamic surface possessing at least two anti-icing/de-icing modules, each module being provided with a respective heater element, wherein the heater elements of said modules are powered electrically via a common electrical power supply means, each anti-icing/de-icing module acting against icing in its own zone independently of the other module(s).

2. A device according to claim 1, wherein at least two heater elements for the same aerodynamic surface are controlled by the same regulator unit.

3. A device according to claim 2, wherein said regulator unit dialogs with at least two heater elements of the same aerodynamic surface via secondary communications means arranged in said aerodynamic surface.

4. A device according to claim 1, wherein each heater element of a common aerodynamic surface is controlled by its own regulator unit.

5. A device according to claim 1, wherein the regulator unit causes electrical power to be supplied to at least one heater element when a first measurement signal from at least one temperature sensor lies below a predetermined trigger threshold.

6. A device according to claim 1, wherein the regulator unit receives a monitoring signal coming from at least one ice sensor, said regulator unit electrically powering said heater element depending on said monitoring signal.

7. A device according to claim 1, wherein said regulator unit is connected to a central processor unit via a main communications means.

8. A device according to claim 1, wherein, for an aerodynamic surface provided with a control unit at its base that is connected to said central processor unit via a main communications means, said control unit is connected to each regulator unit of said aerodynamic surface via said secondary communications means.

9. A device according to claim 1, wherein said central processor unit includes a diagnosis connector element and a central microprocessor together with its memory and interfaces.

10. A device according to claim 1, wherein said regulator unit is made on a flexible medium that is easily integrated in the aerodynamic surface.

11. A device according to claim 1, wherein said temperature sensor is made on a flexible medium.

12. A device according to claim 1, wherein said control unit is made on a flexible medium.

13. A device according to claim 1, wherein said heater element is made on a flexible medium.

14. A device according to claim 1, wherein said heater element comprises a switch member and a heater surface.

15. A device according to claim 1, wherein said heater surface includes at least two heater sections.

16. A device according to claim 1, wherein said electrical power supply means is made in redundant manner.

17. A device according to claim 1, wherein said main communications means is a two-wire bus using a both-way protocol.

18. A device according to claim 1, wherein secondary communications means is a two-wire bus using a both-way protocol.

19. A device according to claim 1, wherein said main and secondary communications means are optical fibers.

20. A device according to claim 1, wherein said main and secondary communications means use a wireless data transmission mode.

21. A device according to claim 1, wherein said electrical power supply means and said main communications means are constituted by a single carrier cable.