ICE RATE METER WITH VIRTUAL ASPIRATION

• US 20080167764A1
• Filed: 01/09/2008
• Published: 07/10/2008
• Est. Priority Date: 01/10/2007
• Status: Abandoned Application

• Current Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Original Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Inventors: Flemming, Robert James
• Application Number:
  US11/971,367
• Publication Number:
  US 20080167764A1
• Time in Patent Office: Days
• US Class Current: 701/14
• CPC Class Codes: B64D 15/20 Means for detecting icing or initiating de-icing

Abstract

A system and method of determining an actual liquid water content (Actual LWC) with an ice rate meter probe without aspiration.

Claims

1. A system for an aircraft comprising:

an ice rate meter probe operable to acquire a measured liquid water content (Measured LWC); and

an ice rate module in communication with said ice rate meter probe, said ice rate module operable to determine a virtual aspiration factor, and to determine a representation of an actual liquid water content using at least said virtual aspiration factor and the Measured LWC, wherein said representation is suitable for use to adjust at least a portion of a deice system.

2. The system as recited in claim 1, wherein said virtual aspiration factor includes a factor which is a function of aircraft airspeed.

3. The system as recited in claim 1, wherein said virtual aspiration factor includes a factor which is a function of outside air temperature.

4. The system as recited in claim 1, wherein said virtual aspiration factor includes a factor which is a function of pressure altitude.

5. The system as recited in claim 1, wherein said virtual aspiration factor includes a factor which is a function of water drop size.

6. The system as recited in claim 1, wherein said virtual aspiration factor includes a factor which is a function of at least one of:

an aircraft airspeed, an outside air temperature, a pressure altitude, or a water drop size.

7. The system as recited in claim 1, wherein said ice rate module is operable to determine said virtual aspiration factor relative to aircraft data.

8. The system as recited in claim 1, further comprising a flight control computer, and wherein said ice rate module is in communication with said flight control computer.

9. The system as recited in claim 8, further comprising a sensor suite in communication with said flight control computer, said sensor suite operable to determine aircraft data.

10. The system as recited in claim 9, wherein said aircraft data includes data representative of an aircraft airspeed and suitable for use by the ice rate module for determination of said virtual aspiration factor.

11. The system as recited in claim 9, wherein said aircraft data includes data representative of a pressure altitude and suitable for use by the ice rate module for determination of said virtual aspiration factor.

12. The system as recited in claim 9, wherein said aircraft data includes data representative of a temperature and suitable for use by the ice rate module for determination of said virtual aspiration factor.

13. The system as recited in claim 9, wherein said aircraft data includes data representative of a supercooled water drop diameter and suitable for use by the ice rate module for determination of said virtual aspiration factor.

14. The system as recited in claim 9, further comprising said deice system in communication with said flight control computer to deice at least one aircraft component, wherein said flight control computer adjusts said deice system based at least in part on information corresponding to said representation.

15. The system as recited in claim 9, further comprising a cockpit display system in communication with said flight control computer.

16. The system as recited in claim 1, further comprising a deice system in communication with said ice rate module to deice at least one aircraft component.

17. The system as recited in claim 16, further comprising a sensor suite in communication with said ice rate module, said sensor suite operable to determine aircraft data wherein said ice rate module adjusts said deice system based at least in part on said aircraft data.

18. The system as recited in claim 1, further comprising a flight control computer, and wherein said ice rate module is in communication with said flight control computer.

19. The system as recited in claim 18, further comprising a sensor suite in communication with said flight control computer, said sensor suite operable to determine aircraft data.

20. The system as recited in claim 19, further comprising a deice system in communication with a flight control computer to deice at least one aircraft component wherein said flight control computer adjusts said deice system based at least in part on said aircraft data.

21. A method comprising:

acquiring measured liquid water content (Measured LWC) data from an ice rate meter probe;

acquiring measured data from an aircraft sensor suite;

correlating a virtual aspiration factor with the measured data from the aircraft sensor suite; and

determining an actual liquid water content (Actual LWC) by applying the virtual aspiration factor to the measured liquid water content data.

22. A method as recited in claim 21, wherein determining the actual liquid water content includes the function:

Actual LWC=a value corresponding to a function of aircraft airspeed×

Measured LWC.

23. A method as recited in claim 21, wherein determining the actual liquid water content includes the function:

Actual LWC=(a value corresponding to a function of aircraft airspeed×

measured LWC)+(a value corresponding to a function of static or total temperature×

measured LWC)+(a value corresponding to a function of pressure altitude×

measured LWC)+(a value corresponding to a function of supercooled water drop diameter×

measured LWC).

24. A method as recited in claim 21, further comprising:

using said actual liquid water content to adjust a deice system.

25. A method as recited in claim 21, further comprising:

communicating a representation of the actual liquid water content to a deice system; and

adjusting the deice system at least in part on said representation

26. A method comprising:

acquiring measured data from an aircraft sensor suite;

multiplying a virtual aspiration factor which is a function of the measured data by a measured liquid water content (Measured LWC) to obtain an actual liquid water content (Actual LWC); and

using said Actual LWC to adjust a deice system of an aircraft.

27. A method as recited in claim 26, wherein the virtual aspiration factor includes a is a function of true airspeed.