DETECTION OF ICING CONDITIONS ON AN AIRCRAFT

• US 20140166813A1
• Filed: 12/14/2012
• Published: 06/19/2014
• Est. Priority Date: 12/14/2012
• Status: Active Grant

• Current Assignee: Safe Flight Instrument Corporation
• Original Assignee: Safe Flight Instrument Corporation
• Inventors: GREENE, Randall A., TETER, Robert D., CORDES, Peter R.
• Granted Patent: US 9,409,649 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

A controller for determining when icing conditions are present on an outside surface of an aircraft may include a first input receiving a moisture condition on a windshield of the aircraft, a second input receiving an outside temperature, and an output that provides an icing condition determined as a function of the first input and the second input. The moisture condition can be provided by a moisture sensor positioned on an interior surface of the windshield and the windshield may include a heating system.

Claims

1. A controller that determines an icing condition on an exterior surface of an aircraft comprising:

a first input that receives a moisture condition on a windshield of the aircraft, wherein the condition is provided by a moisture sensor positioned on an interior surface of the windshield, wherein the windshield comprises a heating system,

a second input that receives an exterior temperature, and

an output that provides an icing condition, wherein the presence of an icing condition is determined as a function of the first input and the second input.

2. The controller of claim 1, wherein the presence of an icing condition is determined when the first input indicates that moisture is present on the windshield and the second input indicates that the exterior temperature is at or below freezing.

3. The controller of claim 1, wherein the moisture condition is determined by utilizing an emitter and a detector relatively positioned so that light from the emitter is refracted at an outer surface of the windshield and detected by the detector.

4. The controller of claim 1, wherein the output comprises a signal to a de-icing or anti-icing system in the aircraft to initiate de-icing or anti-icing.

5. The controller of claim 1, wherein the second input is provided by an air data computer.

6. An aircraft icing condition detector comprising:

a moisture sensor positioned on an interior of a windshield of the aircraft, the windshield comprising a heating system,

an exterior temperature sensor, and

a controller that determines an icing condition as a function of moisture detected by the moisture sensor and temperature detected by the exterior temperature sensor.

7. The aircraft icing condition detector of claim 6, wherein the controller determines an icing condition when the moisture sensor determines moisture is present on the windshield and the exterior temperature sensor determines the exterior temperature is at or below freezing.

8. The aircraft icing condition detector of claim 6, wherein the moisture sensor comprises an emitter and a detector relatively positioned so that light from the emitter is refracted at an outer surface of the windshield and detected by the detector.

9. The aircraft icing condition detector of claim 6, wherein the moisture sensor does not comprise an independent heating system that melts frozen water.

10. The aircraft icing condition detector of claim 6, wherein the controller activates a de-icing or anti-icing system on the aircraft when the controller determines that an icing condition is present.

11. The aircraft icing conditions detector of claim 6, wherein the exterior temperature sensor comprises an probe connected to an air data computer.

12. A method of detecting icing conditions on an aircraft comprising:

determining a presence of moisture on a windshield of the aircraft using a moisture sensor positioned on an interior surface of the windshield, the windshield comprising a heating system,

determining an exterior temperature, and

determining an icing condition as a function of the presence of moisture on the windshield and the exterior temperature.

13. The method of claim 12, wherein determining an icing condition comprises determining a presence of moisture on the windshield and determining if the exterior temperature is at or below freezing.

14. The method of claim 12, wherein determining a presence of moisture on the windshield comprises utilizing an emitter and a detector relatively positioned so that light from the emitter is refracted at an outer surface of the windshield and detected by the detector.

15. The method of claim 12, comprising activating a de-icing or anti-icing system when icing conditions are determined to be present.

16. The method of claim 12, wherein determining the exterior temperature comprises accessing an air data computer for at least one of Outside Air Temperature, Static Air Temperature, Total Air Temperature or RAM air temperature.

18. The method of claim 12 wherein determining a presence of moisture comprises using chirp modulation and pulse compression or signal matching.

17. An aircraft icing condition detector comprising:

a moisture sensor associated with an interior surface of a heatable windshield of the aircraft, an exterior temperature sensor, and a controller that determines an icing condition as a function of moisture detected by the moisture sensor and temperature detected by the exterior temperature sensor.