System and methods for detecting shooter locations from an aircraft

• US 20100020643A1
• Filed: 07/28/2008
• Published: 01/28/2010
• Est. Priority Date: 07/28/2008
• Status: Active Grant

• Current Assignee: Raytheon BBN Technologies Corp. (Rtx Corporation)
• Original Assignee: BBN Technologies (Rtx Corporation)
• Inventors: Ritter, Scott E., Barger, James E.
• Granted Patent: US 8,437,223 B2
• Time in Patent Office: Days
• US Class Current: 367/129
• CPC Class Codes: F41G 3/147 based on detection of a firing weapon
• CPC Class Codes: G01S 3/801 Details G01S3/82, G01S3/84, G01S3/86 take precedence
• CPC Class Codes: G01S 3/8086 determining other position line of source

Abstract

The systems and methods described herein relate to an airborne shooter detection system having a plurality of sensors coupled to the body of an aircraft such as a helicopter. The system includes at least five sensors configured and arranged to disambiguate the location of a shooter. By measuring the arrival times of the shockwaves of projectiles at each of the sensors and determining the differences in the arrival times among sensors, the systems and methods may determine the location of one or more sources of the projectiles. A distance of at least ten meters separates two or more of the sensors. Such a separation is advantageous because it allows the system to disambiguate multiple shooters by resolving the curvature of the shockwave.

Claims

1. An airborne shooter detection system for an aircraft, comprising:

a plurality of sensors spaced apart on the surface of the body of an aircraft configured for receiving signals indicative of one or more characteristics of a shockwave of a projectile;

a processor in communication with a plurality of sensors configured for unambiguously determining the location of the source of the projectile; and

an output device in communication with the processor for outputting the determined location.

2. The system of claim 1, wherein the plurality of sensors includes at least five sensors.

3. The system of claim 2, wherein the plurality of sensors includes about seven sensors.

4. The system of claim 1, wherein the plurality of sensors includes from about 15 to about 18 sensors.

5. The system of claim 1, wherein at least two sensors are separated by a distance sufficient to unambiguously determine the location of the source of the projectile with a probability of greater than about 0.8.

6. The system of claim 1, wherein at least two sensors are separated by a distance from about 8 m to about 11 m.

7. The system of claim 6, wherein at least two sensors are separated by a distance of about 10 m.

8. The system of claim 1, further comprising an aircraft avionics system in communication with the processor.

9. The system of claim 8, further comprising at least one of a temperature sensor and pressure sensor coupled to the aircraft avionics system.

10. The system of claim 9, wherein the processor is configured to receive data from the at least one temperature sensor and pressure sensor via the aircraft avionics system for unambiguously determining the location of the source of the projectile.

11. The system of claim 1, wherein the processor includes a shooter location application for determining the location of the source of the projectile.

12. The system of claim 1, wherein the output device includes at least one of a display, heads-up display (HUD), helmet display, intercom, radio and headset.

22. The system of claim 1, wherein the shockwave corresponds to potentially ambiguous locations for the source of the projectile, and the plurality of sensors are spaced apart on the surface of the body of the aircraft such that for each of a plurality of aircraft orientations, at least 5 sensors can receive the shockwave.

13. An airborne shooter detection system for an aircraft, comprising:

at least five sensors disposed on the body of an aircraft configured for receiving signals indicative of one or more characteristics of a shockwave of a projectile; and

a processor in communication with the sensors configured for determining the location of the source of the projectile;

wherein at least two of the five sensors are separated by a distance of at least 10 m.

14. A method for locating a source of a projectile fired at an aircraft, comprising:

receiving, at a plurality of sensors mounted on an aircraft, signals indicative of one or more characteristics of a shockwave of a projectile fired at the aircraft;

analyzing the signals to unambiguously determine a location of a source of the projectile; and

outputting the location of the source.

15. The method of claim 14, wherein analyzing the signals comprises measuring at least an initial portion of the signals.

16. The methods of claim 14, wherein analyzing the signals further comprises determining from the measured initial portion of the signals Time Differences Of Arrival (TDOA).

17. The method of claim 15, wherein analyzing the signals comprises determining, from the arrival times of the shockwave at the sensors, at least one of the arrival angle, the radius of curvature and the spatial gradient of the radius of curvature of the shockwave.

18. The method of claim 17, wherein the spatial gradient of the radius of curvature is used to unambiguously determine the location of the source of the projectile.

19. The method of claim 14, further comprising receiving data from an aircraft avionics system.

20. The method of claim 19, wherein the data from the aircraft avionics system includes at least one of temperature, attitude, altitude and ground speed.

21. The method of claim 14, wherein the shockwave corresponds to potentially ambiguous locations for the source of the projectile, and the plurality of sensors are mounted on the aircraft such that for each of a plurality of aircraft orientations, at least 5 sensors can receive the shockwave.