LIGHT DETECTION AND RANGING (LIDAR) ICE DETECTION

• US 20180079521A1
• Filed: 06/30/2017
• Published: 03/22/2018
• Est. Priority Date: 09/22/2016
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Jackowski, Jason J., Mackin, Steve G.
• Granted Patent: US 10,214,299 B2
• Time in Patent Office: Days
• CPC Class Codes: B64D 15/08 exuded from surface
• CPC Class Codes: B64D 15/20 Means for detecting icing or initiating de-icing
• CPC Class Codes: B64D 45/00 Aircraft indicators or protectors not otherwise provided for camouflage F41H3/00
• CPC Class Codes: G01B 11/24 for measuring contours or curvatures
• CPC Class Codes: G01S 17/04 Systems determining the presence of a target
• CPC Class Codes: G01S 17/42 Simultaneous measurement of distance and other co-ordinates indirect measurement G01S17/46
• CPC Class Codes: G01S 17/89 for mapping or imaging

Abstract

Method and system to detect ice accumulation on ice prone surfaces of an aircraft. The method and system sweeps a Light Detection and Ranging (LIDAR) beam across ice prone surfaces to measure the shape of the ice prone surfaces. The change in shape of the ice prone surfaces indicates the presence of ice on the ice prone surface.

Claims

1. An ice detector for use of an aircraft, comprising:

a Light Detection and Ranging (LIDAR) device comprising a transmitter and a receiver placed on two distinct locations on the aircraft, such that the LIDAR device measures the shape of an aerodynamic surface on the aircraft in a sweeping manner to detect ice formation.

2. The ice detector of claim 1, wherein:

the transmitter transmits a LIDAR beam to the aerodynamic surface,

the receiver detects the LIDAR beam after the LIDAR beam has reflected off the aerodynamic surface, and

the LIDAR device measures the time of flight of the LIDAR beam between the transmitter and the receiver and uses the time of flight to measure the shape of the aerodynamic surface.

3. The ice detector of claim 2, wherein:

the LIDAR device is positioned inside the aircraft'"'"'s fuselage behind a window,

the transmitter transmits the LIDAR beam through the window, and

the receiver detects the LIDAR beam through the window after the LIDAR beam has reflected off the aerodynamic surface outside the fuselage.

4. The ice detector of claim 2, wherein:

the LIDAR device measures variations of the time of flight in real time and uses the variations to measure changes in the shape of the aerodynamic surface, and

the changes in the shape of the aerodynamic surface are associated with the ice formation on the aerodynamic surface.

5. The ice detector of claim 2, wherein the LIDAR device is mounted on two-axis rotation mount so that the sweeping of the LIDAR beam is in two axes and provides a more complete analysis of the ice formation than an ice detector positioned on the aerodynamic surface.

6. The ice detector of claim 1, further comprising a flight deck indication system alerting flight crew when the ice detector detects ice.

7. The ice detector of claim 1, wherein the aerodynamic surface is a wing.

8. The ice detector of claim 1, wherein the aerodynamic surface is a tail.

9. The ice detector of claim 1, wherein the aerodynamic surface is an engine inlet.

10. A method of detecting ice, comprising:

transmitting a Light Detection and Ranging (LIDAR) beam from an aircraft in a sweeping manner onto an aerodynamic surface of the aircraft, so that the LIDAR beam detects ice formation on the aerodynamic surface.

11. The method of claim 10, further comprising using the LIDAR beam to monitor functioning of an anti-ice system used to anti-ice the aerodynamic surface.

12. The method of claim 10, further comprising:

detecting the ice formation using the LIDAR beam; and

activating an anti-ice system in response to the detecting.

13. The method of claim 10, further comprising:

measuring a time of flight of the LIDAR beam between a transmitter and a receiver; and

using the time of flight to measure a shape of the aerodynamic surface.

14. The method of claim 13, further comprising:

positioning a LIDAR device comprising the transmitter and the receiver inside the aircraft'"'"'s fuselage behind a window, wherein;

the transmitter transmits the LIDAR beam through the window, and

the receiver detects the LIDAR beam through the window after the LIDAR beam has reflected off the aerodynamic surface outside the fuselage.

15. The method of claim 13, further comprising:

measuring variations of the time of flight in real time;

using the variations to measure changes in the shape of the aerodynamic surface; and

associating the changes in the shape with the ice formation.

16. The method of claim 10, wherein the aerodynamic surface is a wing.

17. The method of claim 10, wherein the aerodynamic surface is a tail.

18. The method of claim 10, wherein the aerodynamic surface is an engine inlet.

19. The method of claim 10, wherein the sweeping of the LIDAR beam provides a more complete analysis of the ice formation than an ice detector positioned on the aerodynamic surface.

20. The method of claim 10, further comprising:

alerting flight crew via a flight deck indication when the LIDAR beam detects ice formation; and

the flight crew turning on an anti-ice system and/or to moving the airplane out of the icing condition in response to the flight deck indication.