Probe and integrated ice detection and air data system

• US 6,430,996 B1
• Filed: 05/16/2000
• Issued: 08/13/2002
• Est. Priority Date: 11/09/1999
• Status: Expired due to Term

• Current Assignee: FLYHT Aerospace Solutions Ltd.
• Original Assignee: Optical Detection Systems Inc. (Panasonic Holdings Corporation)
• Inventors: Burns, Joe, Anderson, Mark, Meiners, Larry
• Primary Examiner(s): OEN, WILLIAM L
• Application Number:
  US09/572,017
• Time in Patent Office: 819 Days
• Field of Search: 731/700.2, 731/701.4, 731/702.6, 731/78.R, 731/80, 731/82, 738/666.5, 738/666.6, 735/98, 736/00, 250/227.25, 250/227.28, 250/577, 250/903, 356/128, 356/135, 356/136, 356/137, 340/581, 340/580, 340/583, 340/962, 244/1.R, 244/134.F
• US Class Current: 73/170.26
• CPC Class Codes: B64D 15/20 Means for detecting icing or initiating de-icing
• CPC Class Codes: G01K 13/028 for use in total air temperature [TAT] probes

Abstract

An integrated air data probe capable of measuring pressure, temperature, relative humidity, turbulence, heading, air speed, the presence of ice, and other relevant measurements for use in building a real time map of the aircraft flying conditions. The probe is attached to the external surface of an airplane such as the wing, fuselage or empannage and is adapted to collect and relay these measurements to a receiving station. By utilizing these probes on numerous airplanes, real time data from numerous data points can be mapped to provide pilots and airlines complete information regarding flying conditions. Additionally, the probe includes a recessed surface for detecting the presence, thickness, and continued buildup of ice by mounting the recessed surface directly into the airflow. One or more light beams are passed over and parallel to the recessed surface, and if ice is present the beams are interrupted.

Claims

1. A probe for detecting the presence and thickness of ice, the probe comprising:

a housing in the shape of an airfoil having an outer surface and a recessed surface in said outer surface, said recessed surface including a base portion and first and second side portions extending away from opposite ends of said base portion;

at least one beam emitter to generate a beam, said emitter is positioned to direct said beam from the first side portion of said recessed surface towards the second side portion of said recessed surface; and

at least one beam detector, positioned to detect said beam after said beam has traveled from the first side portion of said recessed surface to the second side portion of said recessed surface.

2. An integrated ice detection and air data system for mounting on an aircraft, comprising in combination:

ice sensing means for detecting the presence and accumulation of ice on an exterior surface of an aircraft, and

air sensing means for monitoring at least one of the air parameters including air pressure, temperature, humidity, and pitot pressure.

3. The data system as set forth in claim 2 wherein said ice sensing means and said air sensing means include a common probe housing having an air data computer connected to said probe housing.

4. The data system as set forth in claim 3 wherein said probe housing has a pitot tube with an inlet opening in the air and coupled to a pressure sensor in said air data computer to sense pitot pressure.

5. The data system as set forth in claim 3 wherein said probe housing has two static ports on opposite sides opening into a static cavity in said housing coupled to a pressure sensor in said air data computer to sense static pressure at the surface of said probe housing.

6. The data system as set forth in claim 3 wherein said probe housing has a temperature and humidity sensor in communication with a hole in the housing to sense temperature and humidity.

7. The data system as set forth in claim 3 wherein said probe housing has an attachment plate for attaching the probe housing to the aircraft.

8. The data system as set forth in claim 3 wherein said probe housing is in the shape of an airfoil.

9. The data system as set forth in claim 8 including an external recessed surface in a leading edge of said airfoil and at least one beam emitter to direct a beam over said recessed surface to a beam detector to provide said ice sensing means.

10. The data system as set forth in claim 3 wherein said probe housing is outside the aircraft and said air data computer is inside the aircraft.

11. The data system as set forth in claim 3 wherein said air data computer calculates ambient pressure surrounding the aircraft from a surface pressure measurement of said probe housing and pitot pressure.

12. The data system as set forth in claim 3 wherein said air data computer calculates ambient temperature corrected for mach heating from surface pressure of said probe housing, pitot pressure, and temperature of said probe housing.

13. The data system as set forth in claim 3 wherein said air data computer calculates indicated air speed from pitot pressure and surface pressure of said probe housing.

14. The data system as set forth in claim 3 wherein said air data computer calculates true airspeed from surface pressure of said probe housing, pitot pressure and temperature of said probe housing.

15. The data system as set forth in claim 3 wherein said air data computer calculates ambient humidity surrounding the aircraft from surface pressure of said probe housing, pitot pressure and temperature of said probe housing.

16. The data system as set forth in claim 3 wherein said air data computer includes accelerometers to calculate turbulence severity.

17. The data system as set forth in claim 3 wherein said air data computer calculates turbulence from fluctuations in pitot pressure.

18. The data system as set forth in claim 3 wherein said air data computer includes a heading sensor providing an output and an input from said air data computer from a global positioning system, said output and input being combined with true airspeed to determine winds aloft speed and direction.

19. The data system as set forth in claim 3 including a global positioning system collecting real time position data from a satellite network operatively associated with an output of said air data computer for detecting the location of the aircraft during the sensing of ice and air data.

20. The data system as set forth in claim 3 wherein said air data computer is coupled to a global positioning system connected to a transmitter for formatting and transmitting air data, position and time information to the ground.

21. An integrated ice detection and air data system for mounting on an aircraft, comprising in combination:

ice sensing means for detecting the presence and accumulation of ice on an exterior surface of an aircraft, and

air sensing means for monitoring of the air parameters including air pressure, temperature and pitot pressure.

22. The data system as set forth in claim 21 including means for monitoring humidity.

23. The data system as set forth in claim 22 wherein said air data computer calculates ambient humidity surrounding the aircraft from surface pressure of said probe housing, pitot pressure and temperature of said probe housing.