Airborne microwave/infrared wind shear and clear air turbulence detector

• US 20040100395A1
• Filed: 11/22/2002
• Published: 05/27/2004
• Est. Priority Date: 11/22/2002
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Anderson, Christopher M.
• Granted Patent: US 6,828,923 B2
• Time in Patent Office: Days
• US Class Current: 340/945
• CPC Class Codes: G01P 13/025 indicating air data, i.e. flight variables of an aircraft, e.g. angle of attack, side slip, shear, yaw
• CPC Class Codes: G01P 5/001 Full-field flow measurement, e.g. determining flow velocity and direction in a whole region at the same time, flow visualisation
• CPC Class Codes: G01P 5/10 by measuring thermal variables

Abstract

A system (24) for detecting an air disturbance in front of an aircraft (10) has a controller (26) that is coupled to an image detector (40). Image detector (40) generates an image signal corresponding to heated air in front of the aircraft (10). The air in front of the aircraft (10) is heated by direct high energy beams such as microwave beams (16, 18) from a respective microwave antenna (12, 14). By monitoring the image, the presence of an air disturbance may be determined. Position adjusters (30, 32) may be used to adjust the position of the beams (16, 18) by controlling the position of antennas (12, 14). The position of the beam is preferably maintained a predetermined distance (d) in front of the aircraft (10) so that an evasive maneuver may be performed.

Claims

1. A method for monitoring an airborne disturbance in front of an airplane comprising:

directing a high energy beam a distance in front of the airplane;

heating the air with the beam;

detecting an image of heated air; and

comparing the image to a profile to determine the presence of a disturbance.

2. A method as recited in claim 1 wherein directing comprises directing a first beam and a second beam in front of the aircraft.

3. A method as recited in claim 1 wherein comprises directing a first beam and a second beam in front of the aircraft comprises focusing the first beam and second beam to substantially a point.

4. A method as recited in claim 1 wherein directing comprises directing the high energy beam a distance as a function of air speed of the vehicle.

5. A method as recited in claim 1 wherein directing comprises changing the distance of the beam as a function of air speed of the aircraft.

6. A method as recited in claim 1 wherein directing comprises directing a microwave beam.

7. A method as recited in claim 1 wherein detecting comprises infrared detecting.

8. A method as recited in claim 1 wherein comparing comprises comparing the image to a profile to determine the presence of turbulence.

9. A method as recited in claim 1 wherein comparing comprises comparing the image to a profile to determine the presence of a wind shear.

10. A system for detecting an air disturbance in front of an aircraft comprising:

a high energy beam generator generating a high energy beam;

an image detector generating an image signal of heated air in front of the aircraft; and

a controller coupled to said image detector, said controller comparing the image to a profile to determine a disturbance.

11. A system as recited in claim 10 wherein said image detector comprises an infrared detector.

12. A system as recited in claim 10 further comprising an indicator, said controller controlling the indicator in response to the disturbance.

13. A system for detecting an air disturbance comprising:

an air speed detector generating an air speed signal;

a first high energy beam generator generating a first high energy beam;

a first position adjuster coupled to first high energy beam generator;

a second energy beam generator generating a second energy beam;

a second position adjuster coupled to second high energy beam generator;

an image detector generating an image signal of heated air in front of the aircraft;

an indicator; and

a controller coupled to said air speed detector, said first position adjuster, said second position adjuster and said image detector, said controller controlling the position of the first beam and the second beam to a location a distance in front of the plane as a function of the air speed signal, said controller receiving image signal and controlling the indicator when the image signal corresponds to a disturbance.

14. A system as recited in claim 13 wherein said indicator comprises an avoidance maneuver control.

15. A system as recited in claim 13 wherein said indicator comprises a visual indicator.

16. A system as recited in claim 13 wherein said indicator comprises an audible indicator.

17. A system as recited in claim 13 wherein the distance corresponds to an avoidance maneuver distance.

18. A system as recited in claim 13 wherein said image detector comprises an infrared detector.

19. A system as recited in claim 13 wherein said air speed detector is a sensor.

20. A system as recited in claim 13 wherein said air speed signal is derived from an aircraft system.