DEVICE AND METHOD FOR DETECTING ICE DEPOSITED ON AN AIRCRAFT STRUCTURE

• US 20120193477A1
• Filed: 01/30/2012
• Published: 08/02/2012
• Est. Priority Date: 01/31/2011
• Status: Active Grant

• Current Assignee: Safran Aerotechnics SAS (Safran SA)
• Original Assignee: Zodiac Aerotechnics
• Inventors: Thorez, Manuel, Paszkiewicz, Laurent
• Granted Patent: US 8,704,181 B2
• Time in Patent Office: Days
• US Class Current: 244/134.F
• CPC Class Codes: B64D 15/20 Means for detecting icing or initiating de-icing

Abstract

The invention relates to an ice detection device and method for detecting ice on an aircraft in flight. The device includes a transmitter which emits a first and a second radiation in the direction of a reflective surface, these two radiations respectively being within a first wavelength band and a second wavelength band; and a receiver which captures the reflected radiations. The transmitter and said receiver are fixed on an external surface of the aircraft. Then a computer determines the presence or absence of ice as a function of the intensity of the captured radiations. The reflective surface is located outside the boundary layer of the aircraft during flight and includes a heating/cooling device.

Claims

1. An ice detection device for an aircraft, said detection device comprising:

at least one transmitter which emits a first radiation and a second radiation in the direction of a reflective surface, said first radiation and said second radiation respectively being within a first wavelength band and a second wavelength band;

a receiver which captures the first radiation and the second radiation reflected by said reflective surface; and

a computer which determines the presence or absence of ice as a function of the intensity of the first radiation and the intensity of the second radiation captured;

wherein said transmitter and said receiver are designed to be attached to an external surface of the aircraft, and wherein the detection device comprises;

a protuberance on which the reflective surface is placed, said reflective surface extending at an angle substantially between 20° and

90°

relative to the external surface of the aircraft, said reflective surface being located outside the boundary layer of the aircraft during flight; and

a heating/cooling device able to exchange heat with at least a portion of said reflective surface.

2. The ice detection device according to claim 1, wherein the heating/cooling device is able to successively heat and cool the reflective surface until the ice respectively disappears and appears, and wherein it comprises a clock which can measure the time between the appearance and disappearance of ice;

said computer being able to determine the severity of the icing conditions as a function of the measured times.

3. The ice detection device according to claim 1, wherein the first wavelength band is between 1.3 μ

m and 1.45 μ

m and the second wavelength band is between 1.5 μ

m and 1.7 μ

m.

4. The ice detection device according to claim 1, wherein said first radiation has a wavelength substantially equal to 1.42 μ

m.

5. The ice detection device according to claim 1, wherein said second radiation has a wavelength substantially equal to 1.55 μ

m.

6. The ice detection device according to claim 1, wherein said protuberance has an aerodynamic shape and, preferably, a shape that is either at least partially cylindrical, a teardrop-shaped cross-section, a shape resembling a half-bean, or an ogive shape supported by a mast.

7. The ice detection device according to claim 1, wherein the heating/cooling device is able to exchange heat with at least an end portion of the protuberance, and said reflective surface is located on said end portion of the protuberance.

8. The ice detection device according to claim 7, wherein said end portion is surrounded by a thermal gasket.

9. Ice detection device according to any one of claim 1, wherein said reflective surface is surrounded by a thermal gasket.

10. An ice detection method for an aircraft, wherein a detection device comprises a transmitter, a receiver, a computer, a heating/cooling device, and a clock;

said method comprising the following steps;

emitting a first radiation and a second radiation in the direction of a reflective surface, with said first radiation and said second radiation respectively being within a first wavelength band and a second wavelength band;

receiving said first radiation and said second radiation reflected by said reflective surface;

determining the absence or presence of ice on the reflective surface as a function of the intensity of the first reflected radiation and the intensity of the second reflected radiation, wherein said method additionally comprises the following steps;

a) cooling the reflective surface until the presence of ice is determined, and measuring the cooling time;

b) heating the reflective surface until the absence of ice is determined, and measuring the heating time;

c) repeating steps a) and b) a predetermined number of times;

d) determining the severity of the ice conditions as a function of the cooling time measured during step a) and the heating time measured during step b).

11. The detection method according to claim 10, wherein the detection device comprises a thermometer, and said method additionally comprises the following steps:

measuring the Total Air Temperature on the reflective surface; and

cooling the reflective surface when the total temperature is between −

10°

C. and +10°

C., and preferably between −

5°

C. and +5°

C.

12. The detection method according to claim 10, wherein the first wavelength band is between 1.3 μ

m and 1.45 μ

m and the second wavelength band is between 1.5 μ

m and 1.7 μ

m.

13. The detection method according to claim 10, additionally comprising the following steps:

a) evaluating the ice thickness by measuring the contrast between the intensity of the first radiation received and the intensity of the second radiation received;

b) repeating step a) after a predefined time;

c) calculating the ice accretion speed; and

d) determining the severity of the ice conditions as a function of the accretion speed.

14. An ice detection method for an aircraft, using a detection device comprising a transmitter, a receiver, a computer, a heating/cooling device, and a clock;

said method comprising the following steps;

emitting a first radiation and a second radiation in the direction of the reflective surface, said first radiation and said second radiation respectively being within a first wavelength band and a second wavelength band;

receiving said first radiation and said second radiation reflected by said reflective surface;

wherein said method additionally comprises the following steps;

a) measuring the contrast between the intensity of the first radiation received and the intensity of the second radiation received;

said measuring step is repeated a predetermined number of times with a predetermined timing until it reaches a predetermined number of steps or a predefined maximum contrast value;

b) calculating the slope of the contrast signal reconstructed from the measurements, and

c) determining the severity of icing conditions according to said slope.

15. An ice detection device for an aircraft, said detection device comprising:

at least one transmitter which emits a first radiation and a second radiation in the direction of a reflective surface of the aircraft, said first radiation and said second radiation respectively being within a first wavelength band and a second wavelength band;

a receiver which captures the first radiation and the second radiation reflected by said reflective surface;

a computer which determines the presence or absence of ice as a function of the intensity of the first radiation and the intensity of the second radiation captured;

wherein the first wavelength band is between 1.3 μ

m and 1.45 μ

m and the second wavelength band is between 1.5 μ

m and 1.7 μ

m, and wherein said transmitter and said receiver are designed to be attached to an external surface of the aircraft, and wherein the detection device comprises;

a protuberance on which the reflective surface is placed, said reflective surface extending at an angle substantially between 20° and

90°

relative to said external surface of the aircraft, said reflective surface being located outside the boundary layer of the aircraft during flight; and

a heating/cooling device able to exchange heat with at least a portion of said reflective surface.