Weather radar system and method

• US 8,159,369 B1
• Filed: 05/28/2009
• Issued: 04/17/2012
• Est. Priority Date: 03/07/2008
• Status: Active Grant

• Current Assignee: Rockwell Collins, Inc. (Rtx Corporation)
• Original Assignee: Rockwell Collins, Inc. (Rtx Corporation)
• Inventors: Koenigs, Gregory J., Finley, Jeffery A., Kronfeld, Kevin M., Bredfeldt, Jeremy S.
• Primary Examiner(s): Nguyen, Phung
• Application Number:
  US12/474,102
• Time in Patent Office: 1,055 Days
• Field of Search: 340/963, 340/949, 340/971, 340/973, 340/974, 340/969, 701/3, 342/63
• US Class Current: 340/963
• CPC Class Codes: B64D 43/00 Arrangements or adaptations of instruments arrangements of cameras B64D47/08; aeronautical measuring instruments per se G01C
• CPC Class Codes: B64D 45/00 Aircraft indicators or protectors not otherwise provided for camouflage F41H3/00
• CPC Class Codes: G01S 13/86 Combinations of radar systems with non-radar systems, e.g. sonar, direction finder
• CPC Class Codes: G01S 13/95 for meteorological use
• CPC Class Codes: G01S 13/953 mounted on aircraft
• CPC Class Codes: G01S 7/02 of systems according to group G01S13/00
• CPC Class Codes: G01S 7/04 Display arrangements
• CPC Class Codes: G01S 7/062 in which different colours are used
• CPC Class Codes: G01S 7/22 Producing cursor lines and indicia by electronic means
• CPC Class Codes: Y02A 90/10 Information and communication technologies [ICT] supporting adaptation to climate change, e.g. for weather forecasting or climate simulation

Abstract

An aircraft hazard warning system configured to provide an indication of a hazard level to an electronic display includes an input configured to receive first input data and second input data. The first input data includes at least one of lightning detection data, radar reflectivity data, turbulence data, geographic location data, vertical structure analysis data, and temperature data. The second input data includes at least one of aircraft speed data and wing loading data. The system further includes processing electronics configured to determine a hazard level of the aircraft based on the first input data. The processing electronics updates at least one characteristic of the hazard level based on the second input data. The processing electronics provides an indication of the hazard level and updated characteristic to the electronic display. For example, the characteristic can be a color of indicators representing the first input data and can be modified based on the second input data.

Claims

1. An aircraft hazard warning system configured to provide an indication of a hazard level to an electronic display, comprising:

an input configured to receive first input data and second input data, the first input data comprising at least one of lightning detection data, radar reflectivity data, turbulence data, geographic location data, vertical structure analysis data, and temperature data, the second input data comprising wing loading data, wherein the wing loading data comprises aircraft configuration data; and

processing electronics configured to determine a hazard level of the aircraft based on the first input data, the processing electronics further configured to update at least one characteristic of the hazard level based on the second input data, the processing electronics providing an indication of the hazard level comprising the updated at least one characteristic to the electronic display;

wherein the aircraft configuration data comprises at least one of flap configuration, landing gear position, speed brake status, spoiler configuration, wing size, and wing geometry.

2. The aircraft hazard warning system of claim 1, wherein the at least one characteristic comprises a color for graphical representation of the hazard level on the electronic display, the color being modified based on the second input data to indicate a severity of the hazard level.

3. The aircraft hazard warning system of claim 1, wherein the at least one characteristic comprises at least one of a line weight, shading, gradient, cross-hatching, and line dashing for graphical representation of the hazard level on the electronic display, the at least one characteristic of the hazard level being modified based on the second input data to indicate a severity of the hazard level.

4. The aircraft hazard warning system of claim 1, wherein the aircraft speed data comprises a sensed aircraft speed.

5. The aircraft hazard warning system of claim 1, wherein the processing electronics is configured to use the altitude data to determine aircraft speed.

6. The aircraft hazard warning system of claim 1, wherein the particle size data indicates a size of at least one of air particles, precipitation, and an obstacle, a larger particle size causing a higher hazard level than a smaller particle size.

7. The aircraft hazard warning system of claim 1, wherein a higher aircraft speed causes a higher hazard level than a lower aircraft speed.

8. The aircraft hazard warning system of claim 1, wherein a lighter wing load causes a higher hazard level than a heavier wing load.

9. A method of providing an indication of a hazard to an electronic aircraft display in an avionics system, comprising:

receiving first input data comprising at least one of lightning detection data, radar reflectivity data, turbulence data, geographic location data, vertical structure analysis data, and temperature data;

receiving second input data comprising wing loading data, wherein the wing loading data comprises aircraft configuration data;

determining a hazard level of the aircraft based on the first input data using processing electronics;

updating at least one characteristic of the hazard level based on the second input data using the processing electronics; and

providing an indication of the hazard level comprising the updated at least one characteristic to the electronic aircraft display,

wherein the aircraft configuration data comprises at least one of flap configuration, landing gear position, speed brake status, spoiler configuration, wing size, and wing geometry.

10. The method of claim 9, wherein the at least one characteristic comprises a color for graphical representation of the hazard level on the electronic aircraft display, the color being modified based on the second input data to indicate a severity of the hazard level.

11. The method of claim 9, wherein the at least one characteristic comprises at least one of a line weight, shading, gradient, cross-hatching, and line dashing for graphical representation of the hazard level on the electronic aircraft display, the at least one characteristic of the hazard level being modified based on the second input data to indicate a severity of the hazard level.

12. The method of claim 9, wherein the aircraft speed data comprises a sensed aircraft speed or wherein the processing electronics is configured to use the altitude data to determine aircraft speed.

13. The method of claim 9, wherein the particle size data indicates a size of at least one of air particles, precipitation, and an obstacle, a larger particle size causing a higher hazard level than a smaller particle size.

14. The method of claim 9, wherein a higher aircraft speed causes a higher hazard level than a lower aircraft speed.

15. The method of claim 9, wherein a lighter wing load causes a higher hazard level than a heavier wing load.

16. An apparatus for providing an indication of a hazard to an aircraft display in an avionics system, comprising:

means for receiving first input data comprising at least one of lightning detection data, radar reflectivity data, turbulence data, geographic location data, vertical structure analysis data, and temperature data;

means for receiving second input data comprising wing loading data, wherein the wing loading data comprises aircraft configuration data;

means for determining a hazard level of the aircraft based on the first input data;

means for updating at least one characteristic of the hazard level based on the second input data; and

means for providing an indication of the hazard level comprising the updated at least one characteristic to the aircraft display;

wherein the aircraft configuration data comprises at least one of flap configuration, landing gear position, speed brake status, spoiler configuration, wing size, and wing geometry.