Aircraft icing conditions detection systems and methods

Patent metadata

Field	Value
Publication number	US-10071808-B1
Application number	US-201715598412-A
Country	US
Kind code	B1
Filing date	May 18, 2017
Priority date	May 18, 2017
Publication date	Sep 11, 2018
Grant date	Sep 11, 2018

Abstract

An icing conditions detection system is configured to detect icing conditions with respect to an aircraft. The icing conditions detection system includes an icing conditions detector secured to a surface of the aircraft and that is configured to detect liquid water within an air stream through which the aircraft flies. A free stream of atmospheric air passes over the icing conditions detector during flight. An icing conditions determination control unit is communicatively coupled to the icing conditions detector, and is configured to detect a first icing condition and a second icing condition based on at least one icing conditions signal received from the icing conditions detector. The first icing condition differs from the second icing condition.

First claim

What is claimed is:

1. An icing conditions detection system that detects icing conditions with respect to an aircraft, the icing conditions detection system comprising:
an icing conditions detector secured to a surface of the aircraft and that detects liquid water within an air stream through which the aircraft flies, wherein a free stream of atmospheric air passes over the icing conditions detector during flight; and
an icing conditions determination control unit communicatively coupled to the icing conditions detector, wherein the icing conditions determination control unit detects a first icing condition and a second icing condition based on at least one icing conditions signal received from the icing conditions detector, wherein the first icing condition differs from the second icing condition, wherein the icing conditions determination control unit is configured to ensure that the icing conditions detector is heated to a temperature that evaporates first water droplets associated with the first icing condition but not second water droplets associated with the second icing condition to differentiate between the first icing condition and the second icing condition.

2. The icing conditions detection system of claim 1 , wherein the first icing condition is an Appendix C icing condition, wherein the second icing condition is an Appendix O icing condition, and wherein the icing conditions determination control unit differentiates between the Appendix C icing condition and the Appendix O icing condition.

3. The icing conditions detection system of claim 1 , further comprising a speed sensor that detects an air speed of the aircraft, wherein the icing conditions determination control unit detects the first icing condition and the second icing condition based on the at least one icing conditions signal received from the icing conditions detector and a speed signal indicative of the air speed of the aircraft received from the speed sensor.

4. The icing conditions detection system of claim 1 , further comprising an altitude sensor that detects an altitude of the aircraft, wherein the icing conditions determination control unit detects the first icing condition and the second icing condition based on the at least one icing conditions signal received from the icing conditions detector and an altitude signal indicative of the altitude of the aircraft received from the altitude sensor.

5. The icing conditions detection system of claim 1 , further comprising an air temperature sensor that detects a temperature of air surrounding the aircraft, wherein the icing conditions determination control unit detects the first icing condition and the second icing condition based on the at least one icing conditions signal received from the icing conditions detector and a temperature signal indicative of the temperature of the air received from the temperature sensor.

6. The icing conditions detection system of claim 1 , further comprising an angle of attack sensor that detects an angle of attack of the surface of the aircraft, wherein the icing conditions determination control unit detects the first icing condition and the second icing condition based on the at least one icing conditions signal received from the icing conditions detector and an angle of attack signal indicative of the angle of attack of the surface of the aircraft received from the angle of attack sensor.

7. The icing conditions detection system of claim 1 , wherein power signal fluctuations of the icing conditions detector are used to detect presence of water impingement on the icing conditions detector.

8. The icing conditions detection system of claim 1 , wherein the icing conditions determination control unit:
detects water content of the air stream, and
analyzes the water content of the atmospheric air in relation to one or more aircraft parameters to determine presence of one or both of the first icing condition and the second icing condition.

9. The icing conditions detection system of claim 8 , wherein the one or more aircraft parameters comprises a speed of the aircraft, altitude of the aircraft, angle of attack of the surface of the aircraft, and atmospheric pressure and temperature.

10. The icing conditions detection system of claim 1 , wherein the icing conditions detector comprises a plurality of chordwise zones, wherein a first portion of the plurality of chordwise zones is within a first icing conditions envelope, and wherein a second portion of the plurality of chordwise zones is within a second icing conditions envelope having portions outside of the first icing conditions envelope.

11. An icing conditions detection method that detects icing conditions with respect to an aircraft, the icing conditions detection method comprising:
detecting liquid water within an air stream through which the aircraft flies by an icing conditions detector that is secured to a surface of the aircraft;
passing a free stream of atmospheric air over the icing conditions detector during flight;
communicatively coupling an icing conditions determination control unit to the icing conditions detector; and
detecting, by the icing conditions determination control unit, a first icing condition and a second icing condition based on at least one icing conditions signal received from the icing conditions detector, wherein the detecting, by the icing condition control unit, comprises ensuring that the icing conditions detector is heated to a temperature that evaporates first water droplets associated with the first icing condition but not second water droplets associated with the second icing condition to differentiate between the first icing condition and the second icing condition.

12. The icing conditions detection method of claim 11 , wherein the first icing condition is an Appendix C icing condition, wherein the second icing condition is an Appendix O icing condition, and wherein the detecting, by the icing conditions determination control unit, comprises differentiating between the Appendix C icing condition and the Appendix O icing condition.

13. The icing conditions detection method of claim 11 , further comprising:
detecting an air speed of the aircraft by a speed sensor,
wherein the detecting, by the icing conditions determination control unit, comprises detecting the first icing condition and the second icing condition based on the at least one icing conditions signal received from the icing conditions detector and a speed signal indicative of the air speed of the aircraft received from the speed sensor.

14. The icing conditions detection method of claim 11 , further comprising:
detecting an altitude of the aircraft by an altitude sensor,
wherein the detecting, by the icing conditions determination control unit, comprises detecting the first icing condition and the second icing condition based on the at least one icing conditions signal received from the icing conditions detector and an altitude signal indicative of the altitude of the aircraft received from the altitude sensor.

15. The icing conditions detection method of claim 11 , further comprising:
detecting a temperature of air surrounding the aircraft by an air temperature sensor,
wherein the detecting, by the icing conditions determination control unit, comprises detecting the first icing condition and the second icing condition based on the at least one icing conditions signal received from the icing conditions detector and a temperature signal indicative of the air temperature received from the air temperature sensor.

16. The icing conditions detection method of claim 11 , further comprising:
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Assignees

• Boeing Co

Inventors

• Bosetti Cris K
• El-Gabalawy Hosam E

Classifications

• B64D15/22 Primary

  Automatic initiation by icing detector · CPC title

• B64D15/12

  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

• B64D15/20 Primary

  Means for detecting icing or initiating de-icing · CPC title