Systems and methods for predicting and controlling ice formation

• US 9,463,879 B2
• Filed: 03/03/2014
• Issued: 10/11/2016
• Est. Priority Date: 03/03/2014
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Khozikov, Vyacheslav, Miller, Robert J., Elangovan, Rangasamy, Matsen, Marc R., Amorosi, Stephen R., Albers, Robert G., Strasik, Michael, Hull, John R.
• Primary Examiner(s): Bonzell, Philip J
• Application Number:
  US14/195,091
• Publication Number:
  US 20150246730A1
• Time in Patent Office: 953 Days
• US Class Current: 1/1
• CPC Class Codes: B64D 15/12 by electric heating electric heating elements in general H05B
• CPC Class Codes: B64D 15/20 Means for detecting icing or initiating de-icing

Abstract

A system and method for operating an ice detection and deicing system are provided herein. The ice detection and deicing system may use changing magnetic properties of various components caused by temperature changes to detect conditions conducive to, or indicating, ice formation. The ice detection and deicing system may further use eddy currents induced in one or more layers of the system to increase the temperature of the one or more layers to reduce the amount of ice formation or reduce the probability of ice being formed.

Claims

1. An ice detection and deicing (“

IDD”

) system, comprising;

a heating susceptor operative to increase temperature in response to an eddy current;

a detecting susceptor having a Curie temperature configured to change its magnetic properties at a desired temperature associated with ice formation;

a coil operative to induce eddy currents in the heating susceptor in response to a change in the magnetic properties of the detecting susceptor as the temperature of the susceptor changes from above the Curie temperature to below the Curie temperature; and

a concentrator operative to interact and modify a magnetic flux created by the coil to focus the magnetic flux towards the heating susceptor.

2. The IDD system of claim 1, further comprising an alternating current power supply operative to energize the coil to provide for a magnetic flux to induce eddy currents in the heating susceptor.

3. The IDD system of claim 1, wherein the heating susceptor and the detecting susceptor comprise a single layer.

4. The IDD system of claim 1, wherein the Curie temperature is selected based on conditions conducive to ice formation.

5. The IDD system of claim 1, wherein the concentrator is further operative to partially insulate one or more locations proximate to the IDD system from the magnetic flux.

6. The IDD system of claim 1, further comprising an insulating layer installed between the detecting susceptor and a composite structure.

7. The IDD system of claim 6, wherein the insulating layer comprises thermal insulation.

8. The IDD system of claim 1, further comprising an erosion shield operative to reduce erosion of various components of the IDD system.

9. The IDD system of claim 8, wherein the erosion shield comprises aluminum, steel, titanium, or other corrosion resistant ferrite metals or metallic alloys.

10. A method for operating an ice detection and deicing system, the method comprising:

coupling one or more susceptors to an exterior of an aircraft external flight surface;

positioning a coil on an opposite side of the composite structure;

positioning a concentrator proximate to the coil;

operating an aircraft having the one or more susceptors on the aircraft external flight surface;

detecting a change in a magnetic property of the one or more susceptors caused by a reduction in temperature of the one or more susceptors below a Curie temperature of the one or more susceptors;

calculating a temperature change based on the change in the magnetic property;

determining a probability of ice formation on the aircraft external flight surface;

inducing eddy currents into the one or more susceptors to generate heat within the one or more susceptors;

maintaining the induction of eddy currents until a set point is reached; and

removing the induced eddy currents once the set point is reached.

11. The method of claim 10, wherein the concentrator comprises a ferrite material.

12. The method of claim 10, further comprising coupling a thermal insulation layer between the one or more susceptors and the composite structure.

13. The method of claim 10, further comprising operating an aircraft having one or more susceptors to an aircraft external flight surface and incorporating a coil connected to a power supply, the coil and power supply operative to create a magnetic flux to detect a change in a magnetic property of the one or more susceptors and to increase the temperature of the one or more susceptors by inducing eddy currents in the one or more susceptors.

14. The method of claim 13, further comprising operating an aircraft coupling an erosion shield to an exterior of the one or more susceptors.

15. An aircraft wing leading edge, comprising:

an erosion shield operative to reduce erosion;

a heating susceptor operative to be responsive to eddy current formation, causing the temperature of the heating susceptor to increase;

a detecting susceptor having a Curie temperature used to indicate a change in temperature of the detecting susceptor;

a composite structure operative to support one or more components of the ice detection and deicing systems;

an insulating layer installed between the detecting susceptor and the composite structure;

a coil operative to induce eddy currents in the heating susceptor;

an alternating current power supply operative to energize the coil to provide for a magnetic flux to induce eddy currents in the heating susceptor to increase the temperature of the heating susceptor; and

a concentrator operative to interact and modify a magnetic flux created by the coil to focus the magnetic flux towards the heating susceptor.

16. The aircraft wing leading edge of claim 15, wherein the erosion shield comprises aluminum, steel, titanium, or other corrosion resistant ferrite metals or metallic alloys.

17. The aircraft wing leading edge of claim 15, wherein the heating susceptor and the detecting susceptor comprise a single layer.

18. The aircraft wing leading edge of claim 15, wherein the concentrator is further operative to partially insulate one or more locations proximate to the coil from the magnetic flux.