Radar velocity determination using direction of arrival measurements

Patent metadata

Field	Value
Publication number	US-9846229-B1
Application number	US-201514645131-A
Country	US
Kind code	B1
Filing date	Mar 11, 2015
Priority date	Mar 11, 2015
Publication date	Dec 19, 2017
Grant date	Dec 19, 2017

Abstract

The various technologies presented herein relate to utilizing direction of arrival (DOA) data to determine various flight parameters for an aircraft A plurality of radar images (e.g., SAR images) can be analyzed to identify a plurality of pixels in the radar images relating to one or more ground targets. In an embodiment, the plurality of pixels can be selected based upon the pixels exceeding a SNR threshold. The DOA data in conjunction with a measurable Doppler frequency for each pixel can be obtained. Multi-aperture technology enables derivation of an independent measure of DOA to each pixel based on interferometric analysis. This independent measure of DOA enables decoupling of the aircraft velocity from the DOA in a range-Doppler map, thereby enabling determination of a radar velocity. The determined aircraft velocity can be utilized to update an onboard INS, and to keep it aligned, without the need for additional velocity-measuring instrumentation.

First claim

What is claimed is:

1. An aircraft radar system comprising:
a comparator component configured to:
identify a first pixel in a first radar image;
identify a second pixel in a second radar image, wherein the first pixel and the second pixel both correlate to a target illuminated by the radar system;
obtain first Doppler frequency information and a first squint angle for the first pixel and second Doppler frequency information and a second squint angle for the second pixel;
identify a relationship between the first pixel and the second pixel, wherein the relationship is a function of the first Doppler frequency information, the first squint angle, the second Doppler frequency information, and the second squint angle; and
determine, based upon the identified relationship between the first pixel and the second pixel, an actual velocity of the aircraft.

2. The aircraft radar system of claim 1 , wherein the comparator component is further configured, as a function of the identification of the relationship between the first pixel and the second pixel, to:
determine a first coordinate which represents the first Doppler frequency information and the first squint angle;
determine a second coordinate which represents the second Doppler frequency information and the second squint angle;
determine a best fit line between the first coordinate and the second coordinate; and
determine, from a slope of the best fit line, the actual velocity of the aircraft.

3. The aircraft radar system of claim 1 , further comprising a navigator component, wherein the navigator component is configured to determine an initial velocity of the aircraft.

4. The aircraft radar system of claim 3 , wherein the comparator component is configured to communicate the actual velocity of the aircraft to the navigator component.

5. The aircraft radar system of claim 4 , wherein the navigator component is further configured to update the initial velocity of the aircraft by replacing the initial velocity of the aircraft with the actual velocity of the aircraft received from the comparator component.

6. The aircraft radar system of claim 1 , wherein the comparator component is further configured to update the first radar image or the second radar image with the determined actual velocity of the aircraft.

7. The aircraft radar system of claim 1 , wherein the first pixel has a signal to noise ratio greater than a threshold value and the second pixel has a signal to noise ratio greater than the threshold value.

8. The aircraft radar system of claim 1 , wherein the radar system further comprises a monopulse antenna to illuminate the target.

9. A method for determining aircraft velocity for an aircraft, comprising:
selecting a first pixel in a first range-Doppler map, wherein the first pixel includes first data comprising a first Doppler frequency and a first squint angle, and the first range-Doppler map is obtained from radar data collected by a radar system located on the aircraft;
selecting a second pixel in the first range-Doppler map, wherein the second pixel includes second data comprising a second Doppler frequency and a second squint angle;
selecting a third pixel in a second range-Doppler map, wherein the first pixel and the third pixel both correlate to a target illuminated by the radar system, the third pixel includes third data comprising a third Doppler frequency and a third squint angle;
selecting a fourth pixel in the second range-Doppler map, wherein the second pixel and the fourth pixel both correlate to a target illuminated by the radar system, the fourth pixel includes fourth data comprising a fourth Doppler frequency and a fourth squint angle;
determining a first coordinate representing a first difference between the first Doppler frequency and the third Doppler frequency and a second difference between the first squint angle and the third squint angle;
determining a second coordinate representing a third different between the second Doppler frequency and the fourth Doppler frequency and a fourth difference between the second squint angle and the fourth squint angle;
determining a best fit line between the first coordinate and the second coordinate; and
determining, from a slope of the best fit line, the aircraft velocity.

10. The method for determining aircraft velocity for an aircraft of claim 9 , further comprising updating a navigator system on the aircraft with the aircraft velocity.

11. The method for determining aircraft velocity for an aircraft of claim 9 , further comprising correcting a synthetic aperture radar image generated by the radar system, the correcting being in accordance with the determined aircraft velocity.

12. The method for determining aircraft velocity for an aircraft of claim 9 , further comprising determining an intercept of the best fit line and a squint angle axis to obtain a squint angle identifying an alignment of an antenna of the radar system to the target.

13. The method for determining aircraft velocity for an aircraft of claim 12 , wherein the target is stationary.

14. The method for determining aircraft velocity for an aircraft of claim 9 , further comprising determining an intercept of the best fit line and a Doppler frequency axis to obtain an antenna beam boresight for an alignment of an antenna of the radar system to the target.

15. The method for determining aircraft velocity for an aircraft of claim 9 , wherein the aircraft is in straight and level flight.

16. The method for determining aircraft velocity for an aircraft of claim 9 , wherein the first pixel, the second pixel, the third pixel, and the fourth pixel each have a signal to noise ratio greater than a threshold value.

17. An integrated circuit configured to perform acts, the acts comprising:
selecting a first pixel in a first range-Doppler map, wherein the first pixel includes first data comprising a first Doppler frequency and a first squint angle, and the first range-Doppler map is obtained from radar data collected by a radar system located on the aircraft;
selecting a second pixel in the first range-Doppler map, wherein the second pixel includes second data comprising a second Doppler frequency and a second squint angle;
selecting a third pixel in a second range-Doppler map, wherein the first pixel and the third pixel both correlate to a target illuminated by the radar system, the third pixel includes third data comprising a third Doppler frequency and a third squint angle;
selecting a fourth pixel in the second range-Doppler map, wherein the second pixel and the fourth pixel both correlate to the target illuminated by the radar system, the fourth pixel includes fourth data comprising a fourth Doppler frequency and a fourth squint angle;
determining a first coordinate representing a first difference between the first Doppler frequency and the third Doppler frequency and a second difference between the first squint angle and the third squint angle;
determining a second coordinate representing a third different between the second Doppler frequency and the fourth Doppler frequency and a fourth difference between the second squint angle and the fourth squint angle;
determining a best fit line between the first coordinate and the second coordinate; and
determining, from a slope of the best fit line, the aircraft velocity.

18. The integrated circuit of claim 17 , further comprising determining from an intercept of the best fit line and a squint angle axis to obtain a squint angle identifying an alignment of an antenna of the radar system to the target.

Assignees

• Nat Tech & Eng Solutions Sandia Llc
• Nat Tech & Eng Solutions Sandia Llc

Inventors

• Doerry Armin W
• Bickel Douglas L
• Naething Richard M
• Horndt Volker

Classifications

• G01S2013/9041

  Physics · mapped topic

• G01S13/9035 Primary

  Physics · mapped topic

• G01S13/605

  using a pattern, backscattered from the ground, to determine speed or drift by measuring the time required to cover a fixed distance · CPC title

• G01S13/9092

  combined with monopulse techniques · CPC title

• G01S13/9019

  Auto-focussing of the SAR signals · CPC title