Accurate range-to-go for command detonation

Patent metadata

Field	Value
Publication number	US-11199387-B2
Application number	US-201816123269-A
Country	US
Kind code	B2
Filing date	Sep 6, 2018
Priority date	Sep 6, 2018
Publication date	Dec 14, 2021
Grant date	Dec 14, 2021

Abstract

The system and method for accurately determining range-to-go for the command detonation of a projectile. Using dual laser and/or radio frequency detectors on the tail and on the nose of a spinning projectile to determine the range-to-go, time-to-go, or lateral offset from the projectile to the target.

First claim

What is claimed:

1. A method for controlling detonation, comprising:
providing a projectile comprising a tail portion and a front portion;
detecting a laser signal via a tail detector mounted about the tail portion of the projectile;
determining a first time at which the laser signal is detected via the tail detector;
detecting a reflected laser signal via a front detector mounted on the front portion of the projectile, the reflected laser signal being the laser signal that has reflected off a target;
determining a second time at which the reflected laser signal is detected via the front detector;
comparing the first time to the second time to determine a time delay;
determining a lateral offset between the projectile and the target using the time delay; and
determining an angle, theta, using the time delay to determine the detonation of the projectile,
wherein the first signal further comprises a first pulse repetition interval and the second signal further comprises a second pulse repetition interval, and
wherein the lateral offset between the projectile's trajectory and the target's actual position is determined by measuring a time expansion between the first pulse repetition interval and the second pulse repetition interval and convolving the projectile's velocity with the time-to-go thereby improving an accuracy of a detonation.

2. The method for controlling detonation according to claim 1 , wherein the tail detector is an electro-optical PIN diode.

3. The method for controlling detonation according to claim 1 , wherein the front detector is an array PIN diode.

4. The method for controlling detonation according to claim 1 , wherein a range finding clock is started when the first signal is detected (T zero ) by the tail detector and the range finding clock is stopped when the reflected signal is detected by the front detector (T reflected ), thereby creating a time differential that represents a round trip time between the projectile and the target and converting to a range-to-go.

5. The method for controlling detonation according to claim 1 , wherein when a detonation time-to-go is about 0.005 seconds, sending a signal to the projectile to cause the detonation.

6. The method for controlling detonation according to claim 5 , wherein determining the time-to-go determination is dependent on the projectile speed and the detonation time-to-go is programmed at the time of launch.

7. The method for controlling detonation according to claim 5 , wherein the time-to-go value is negative.

8. The method for controlling detonation according to claim 1 , further comprising calculating theta-dot.

9. The method for controlling detonation according to claim 1 , further comprising calculating theta double dot.

10. The method for controlling detonation according to claim 9 , wherein taking a first derivative with respect to time minus angular velocity results in theta-dot or taking a second derivative with respect to time minus angular acceleration results in theta double dot, further comprising using theta-dot or theta double dot without the range-to-go calculation to determine the optimum detonating distance using a Kalman filter.

11. A method for controlling detonation, comprising:
providing a projectile comprising a tail portion and a front portion;
detecting a first RF signal via a tail detector mounted on the tail portion of the projectile;
determining a first time at which the first RF signal is detected via the tail detector;
detecting a reflected RF signal via a front detector mounted on the front portion of the projectile, the reflected RF signal being the first RF signal that has reflected off a target;
determining a second time at which the reflected RF signal is detected via the front detector;
comparing the first time to the second time to determine a time delay;
determining a lateral offset between the projectile and the target; and
determining an angle, theta, using the time delay between detection by the tail detector and detection by the front detector to accurately control the detonation,
wherein the first signal further comprises a first pulse repetition interval and the reflected signal further comprises a second pulse repetition interval, and
wherein the lateral offset between the projectile's trajectory and the target's actual position is determined by measuring a time expansion between the first pulse repetition interval and the second pulse repetition interval and convolving the projectile's velocity with the time-to-go thereby improving an accuracy of a detonation.

12. The method for controlling detonation according to claim 11 , wherein the detector on the tail and/or the nose of the projectile is a radio frequency antenna.

13. The method for controlling detonation according to claim 11 , wherein a range finding clock is started when the first RF signal is detected (T zero ) by the tail detector and the range finding clock is stopped when the reflected signal is detected by the front detector (T reflected ), thereby creating a time differential that represents a round trip time between the projectile and the target, and converting to a range-to-go.

14. The method for controlling detonation according to claim 13 , wherein when the time-to-go is time about 0.0015 seconds, sending a signal to cause the projectile to detonate.

15. The method for controlling detonation according to claim 13 , wherein the time-to-go determination is dependent on the projectile speed and the detonation time-to-go is programed at the time of launch.

16. The method for controlling detonation according to claim 13 , wherein the time-to-go value is negative.

17. The method for controlling a detonation according to claim 11 , further comprising calculating theta-dot and/or theta double dot, wherein the theta dot is derived by taking a first derivative with respect to time minus angular velocity and theta double dot is derived by taking the second derivative with respect to time minus angular acceleration, and wherein the theta-dot and/or theta double dot is used without the range-to-go calculation to determine the optimum detonating distance using a Kalman filter.

18. A system for controlling detonation, the system comprising:
a projectile comprising a tail portion and a front portion, including a tail detector mounted proximate the tail portion and a front detector proximate the front portion; and
a processor in communication with the projectile, the processor configured to:
detect a first RF signal via the tail detector;
determining a first time at which the first RF signal is detected via the tail detector;
detecting a reflected RF signal via the front detector, the reflected RF signal being the first RF signal that has reflected off a target;
determining a second time at which the reflected RF signal is detected via the front detector;
comparing the first time to the second time to determine a time delay;
determining a lateral offset between the projectile and the target; and
determining an angle, theta, using the time delay between detection by the tail detector and detection by the front detector to accurately control the detonation,
wherein the first signal further comprises a first pulse repetition interval and the reflected signal further comprises a second pulse repetition interval, and
wherein the lateral offset between the projectile's trajectory and the target's actual position is determined by measuring a time expansion between the first pulse repetition interval and the second pulse repetition interval and convolving the proje

Assignees

• Bae Sys Inf & Elect Sys Integ

Inventors

• Choiniere Michael J
• Winker Bruce

Classifications

• F42B15/01 Primary

  Arrangements thereon for guidance or control ({steering arrangements F42B10/60}; aircraft flight control B64C; guidance systems other than those installed aboard F41G7/00, F41G9/00; locating by use of radio or other waves G01S; flight control in general G05D1/00; computer aspects G06]) · CPC title

• F41G7/2293

  using electromagnetic waves other than radio waves · CPC title

• F42C13/04 Primary

  operated by radio waves · CPC title

• F41G7/222

  for spin-stabilized missiles · CPC title

• F41G7/2266

  Systems comparing signals received from a base station and reflected from the target · CPC title