De-ice and anti-ice system and method for aircraft surfaces

• US 6,194,685 B1
• Filed: 07/30/1999
• Issued: 02/27/2001
• Est. Priority Date: 09/22/1997
• Status: Expired due to Fees

• Current Assignee: Kelly Aerospace Thermal Systems, LLC
• Original Assignee: Northcoast Technologies, Limited
• Inventors: Rutherford, Robert B.
• Primary Examiner(s): Hoang, Tu Ba
• Application Number:
  US09/364,388
• Time in Patent Office: 578 Days
• Field of Search: 219/201, 219/202, 219/535, 219/548, 219/553, 219/200, 219/203, 244/123, 244/133, 244/134.E, 244/134.D, 244/134.R
• US Class Current: 219/201
• CPC Class Codes: B64D 15/14 controlled cyclically along length of surface

Abstract

A thermal de-ice and anti-ice system for aircraft surfaces employs a laminate in which flexible expanded graphite foil is an electrical and heat conducting layer that is disposed below an outer heat conducting layer, with an electrically insulating layer below the graphite layer. The flexible expanded graphite layer requires about three times less wattage than known resistance heating pad thermal systems to achieve de-ice and/or anti-ice temperatures. The temperature of the surface is controlled by varying the power supplied to the flexible expanded graphite layer of the laminate in response to a real time temperature value transmitted to a power control.

Claims

1. A system for electrothermally preventing the formation of ice on or removing ice from a surface of an aircraft during flight, comprising:

a heat-conducting tape bonded to an outer surface of an aircraft, wherein the outer surface includes a leading edge, the heat-conducting tape comprising at least two layers laminated to each other under heat and pressure, the layers comprising (i) a non-metallic electrical and heat conductive layer connected to a power source, the non-metallic conductive layer consisting of a continuous flexible expanded graphite foil sheet, and (ii) an outer heat-conducting layer that is an electrical insulator, having a thermal conductivity of about 0.1 W/M°

K to about 5 W/M°

K;

a power source;

an electronic connection for connecting the flexible expanded graphite foil sheet to the power source;

a programmable power control for controlling the delivery of electrical energy from the power source to the flexible expanded graphite foil sheet;

a temperature sensor in communication with an outer surface of the heat conducting layer and in electronic communication with the power control for real time transmitting to the power control of a value representing the temperature of the outer surface of the heat conducting layer, wherein the power control further comprises a receiving unit for receiving the real time temperature value;

wherein the power control is programmed to store a predetermined reference temperature range;

the power control is further programmed to compare the received real time temperature value with the predetermined reference temperature range;

the power control is further programmed to indicate an acceptable temperature when the received temperature value falls within the reference range; and

the power control is further programmed to signal the power source to provide more or less electrical energy to the flexible expanded graphite layer of the laminate when the received temperature falls outside the reference temperature range.

2. The system of claim 1, further comprising a sensor for sensing icing conditions when ice-producing combinations of ambient temperature, humidity and dew point exist in the atmosphere encountered by the aircraft, said sensor being programmed to signal the power source to provide electrical energy to the flexible expanded graphite foil sheet when icing conditions are sensed.

3. An aircraft comprising the system of claim 1.

4. An aircraft comprising the system of claim 2.

5. The system of claim 1, wherein the flexible expanded graphite foil sheet has a thickness of about 0.003 to about 0.125 inches.

6. The system of claim 5, wherein the foil sheet has a thickness of about 0.025 to about 0.125 inches.

7. The system of claim 5, wherein the foil sheet has a thickness of about 0.003 to about 0.070 inches.

8. The system of claim 7, wherein the foil sheet has a thickness of about 0.003 to about 0.030 inches.

9. The system of claim 1, wherein the flexible expanded graphite foil sheet has a specific resistivity of about 1×

10<sup>−

4</sup> to about 10×

10<sup>−

4</sup> ohm-inches.

10. The system of claim 9, wherein the foil sheet has a specific resistivity of about 2.8×

10<sup>−

4</sup> to about 7.5×

10<sup>−

4</sup> ohm-inches.

11. The system of claim 10, wherein the foil sheet has a specific resistivity of about 3.1×

10<sup>−

4</sup> to about 6.5×

10<sup>−

4</sup> ohm-inches.

12. The system of claim 1, wherein the flexible expanded graphite foil sheet has a density of about 50 to about 90 lbs./ft.³.

13. The system of claim 12, wherein the flexible expanded graphite foil sheet has a density of about 70 lbs./ft.³.

14. The system of claim 1, wherein the outer heat-conducting layer comprises a thermoplastic or a thermosetting material and an inorganic filler that conducts heat.

15. The system of claim 14, wherein the inorganic filler is selected from the group consisting of aluminum nitride, boron nitride, alumina, silicon nitride, and mixtures thereof.

16. The system of claim 14, wherein the material comprises polyurethane.

17. The system of claim 1, wherein the outer heat-conducting layer has a thermal conductivity of 0.5 W/M°

K to about 4 W/M°

K.

18. The system of claim 1, wherein the outer heat-conducting layer has a thickness of about 0.001 to about 0.030 inches.

19. The system of claim 18, wherein the outer heat-conducting layer has a thickness of about 0.001 to about 0.010 inches.

20. The system of claim 1, wherein the heat-conducting tape further comprises an electrically insulating layer, wherein the flexible expanded graphite foil sheet is disposed between the outer heat-conducting layer and the insulating layer.

21. The system of claim 20, wherein the insulating layer is a component of the heat-conducting tape or is a component of the outer surface of the aircraft.

22. The system of claim 20, wherein the insulating layer is a heat insulator.

23. The system of claim 20, wherein the insulating layer has a thickness of about 0.005 to about 0.250 inches.

24. The system of claim 20, wherein the electrically insulating layer is bonded to the flexible expanded graphite foil sheet with an adhesive.