Apparatuses and methods for anti-icing of speed measurement probes

Patent metadata

Field	Value
Publication number	US-10160548-B2
Application number	US-201614987318-A
Country	US
Kind code	B2
Filing date	Jan 4, 2016
Priority date	Jan 4, 2016
Publication date	Dec 25, 2018
Grant date	Dec 25, 2018

Abstract

A de-icing system is provided that includes a member, a coil, and a power supply. The member includes an anti-icing portion. The coil is inductively coupled to the anti-icing portion of the member. The power supply is coupled to the coil, and is configured to provide voltage to the coil. The coil emits electromagnetic energy responsive to power supplied by the power supply. Responsive to the electromagnetic energy, eddy currents are generated in the anti-icing portion that provide heating of the anti-icing portion.

First claim

What is claimed is:

1. A de-icing system comprising:
a member including an anti-icing portion, the member comprising a pitot tube having a static cavity and a pitot cavity, the static cavity and the pitot cavity coupled to a pressure difference meter, wherein the static cavity radially surrounds the pitot cavity, the anti-icing portion including a cylindrically shaped portion;
a coil inductively coupled to the anti-icing portion of the member, wherein the coil inductively heats the cylindrically shaped portion of the anti-icing portion, wherein the coil is radially inward of a wall of the static cavity, a wall of the pitot cavity is radially inward of the coil, and the cylindrically shaped portion of the anti-icing portion is radially inward of the wall of the pitot cavity; and
a power supply coupled to the coil, the power supply configured to provide voltage to the coil, wherein the coil emits electromagnetic energy responsive to power supplied by the power supply, wherein, responsive to the electromagnetic energy, eddy currents are generated in the anti-icing portion that provide heating of the anti-icing portion.

2. The system of claim 1 , wherein the anti-icing portion includes an anti-icing heating surface comprising a smart suscepting alloy.

3. The system of claim 1 , wherein the coil and the anti-icing portion are disposed on opposite sides of the member.

4. The system of claim 1 , wherein the pitot tube comprises a support, the anti-icing portion comprising a portion that inductively heats a surface of the support.

5. The system of claim 1 , wherein the coil has a varying pitch along an axis of the pitot cavity.

6. The system of claim 1 , wherein the system comprises a flat coil, wherein the pitot tube comprises a support, the anti-icing portion comprising an anti-icing heating portion that is disposed proximate a leading edge of the support and that inductively heats a surface of the support via the flat coil.

7. The system of claim 1 , wherein the pitot tube is configured to be disposed on an exterior of an aircraft, the power supply configured to be disposed in a pressurized area of an interior of the aircraft.

8. The system of claim 1 , wherein the pitot tube is configured to be disposed on an exterior surface of an aircraft, wherein the power supply is disposed on an opposing interior surface of the aircraft.

9. The system of claim 1 , wherein the pitot tube is configured to be disposed on an exterior of an aircraft, wherein the system further comprises an inverter inside the pitot tube, the inverter in electrical communication with a direct current (DC) input.

10. A method comprising:
providing a member including an anti-icing portion, the member comprising a pitot tube having a static cavity and a pitot cavity, the static cavity and the pitot cavity coupled to a pressure difference meter, wherein the static cavity radially surrounds the pitot cavity, the anti-icing portion including a cylindrically shaped portion;
inductively coupling a coil to the anti-icing portion of the member, wherein the coil inductively heats the cylindrically shaped portion of the anti-icing portion, wherein the coil is radially inward of a wall of the static cavity, a wall of the pitot cavity is radially inward of the coil, and the cylindrically shaped portion of the anti-icing portion is radially inward of the wall of the pitot cavity; and
coupling a coil to a power supply, the power supply configured to provide voltage to the coil, wherein the coil emits electromagnetic energy responsive to power supplied by the power supply, wherein, responsive to the electromagnetic energy, eddy currents are generated in the anti-icing portion that provide heating of the anti-icing portion.

11. The method of claim 10 , wherein the anti-icing portion includes an anti-icing heating surface comprising a smart suscepting alloy.

12. The method of claim 11 , wherein providing the member includes at least one of vapor depositing the smart suscepting alloy on the anti-icing portion, electroplating to deposit the smart suscepting alloy, or embedding the smart suscepting alloy in the anti-icing portion.

13. The method of claim 10 , wherein the pitot tube comprises a support, the anti-icing portion comprising a portion that inductively heats a surface of the support.

14. The method of claim 10 , further comprising providing a variable pitch in the coil.

15. The method of claim 10 , wherein the pitot tube comprises a support, the anti-icing portion comprising an anti-icing heating portion that inductively heats a surface of the support, the method comprising disposing the anti-icing heating portion proximate a leading edge of the support that is heated by a flat coil.

16. A method comprising:
providing a voltage to a coil from a power supply;
generating an eddy current responsive to the voltage in an anti-icing portion of a member inductively coupled to the coil, wherein the member comprises a pitot tube having a static cavity and pitot cavity, the static cavity and the pitot cavity coupled to a pressure difference meter, wherein the static cavity radially surrounds the pitot cavity, the anti-icing portion including a cylindrically shaped portion, wherein the coil is radially inward of a wall of the static cavity, a wall of the pitot cavity is radially inward of the coil, and the cylindrically shaped portion of the anti-icing portion is radially inward of the wall of the pitot cavity; interposed between the pitot cavity and the coil; and
providing heating to de-ice the cylindrically shaped portion via the eddy current.

17. The method of claim 16 , wherein the anti-icing portion includes an anti-icing heating surface comprising a smart suscepting alloy.

18. The method of claim 16 , wherein the anti-icing portion includes an anti-icing heating surface disposed proximate a boundary of the pitot cavity.

19. The method of claim 16 , wherein the pitot tube comprises a support, the anti-icing portion including an anti-icing heating surface disposed proximate a leading edge of the support that is heated by a flat coil.

Assignees

• Boeing Co

Inventors

• Dichek Daniel Jonathan Gunnar
• Khozikov Vyacheslav
• Morrow Jonathan

Classifications

• B64D15/12 Primary

  by electric heating (heating arrangements specially adapted for transparent or reflecting areas H05B3/84) · CPC title

• B64D43/02

  for indicating aircraft speed or stalling conditions · CPC title

• G01P1/00

  Details of instruments · CPC title

• G01P5/165 Primary

  Arrangements or constructions of Pitot tubes · CPC title