Constraining navigational drift in a munition

Patent metadata

Field	Value
Publication number	US-11913757-B2
Application number	US-202217578006-A
Country	US
Kind code	B2
Filing date	Jan 18, 2022
Priority date	Jan 18, 2022
Publication date	Feb 27, 2024
Grant date	Feb 27, 2024

Abstract

A method and system for constraining navigational drift in a munition caused by Inertial Measurement Unit (IMU) bias error during flight of the munition in a constellation of a plurality of munitions in a Global Positioning System (GPS) denied attack. Each munition is provided with a datalink communication system to communicate with other munitions in the constellation and a navigation system having an IMU for guiding the munition in flight. An estimated position and covariance of the estimated position is determined for each munition via each munitions' navigation system. A range of each munition relative to at least one other munition in the munition constellation is determined via each munitions' datalink communication system. The estimated position and range to at least one other munition in the munition constellation is shared by each munition via each munitions' datalink communication system. Navigational drift for each munition is determined utilizing the estimated position of at least one other munition and the range to that at least one other munition in the munition constellation. And navigational drift in each munition is constrained by compensating for IMU bias error in each munition utilizing the determined navigational drift for each respective munition in the munition constellation.

First claim

What is claimed is:

1. A method for constraining navigational drift in a munition caused by Inertial Measurement Unit (IMU) bias error during flight of the munition in a constellation of a plurality of munitions in a Global Positioning System (GPS) denied attack of a plurality of ground targets wherein each munition is provided with a datalink communication system to communicate with other munitions in the constellation and a navigation system having an IMU for guiding the munition in flight, the method comprising:
determining an estimated position and covariance of the estimated position in each munition in the munition constellation via each munitions' navigation system;
determining a range of each munition relative to at least one other munition in the munition constellation via each munitions' datalink communication system;
sharing the estimated position and range to at least one other munition in the munition constellation by each munition via each munitions' datalink communication system;
determining navigational drift for each munition via each munitions' navigation system utilizing the estimated position of at least one other munition and the range to that at least one other munition in the munition constellation; and
constraining navigational drift in each munition by compensating for IMU bias error in each munition utilizing the determined navigational drift for each respective munition in the munition constellation.

2. The method for constraining navigational drift in a munition as recited in claim 1 , wherein an Extended Kalman Filter (EKF) is utilized by each navigation system of each munition for determining an estimated position and covariance of the estimated position for each respective munition in the munition constellation.

3. The method for constraining navigational drift in a munition as recited in claim 1 , wherein an Unscented Kalman Filter (UKF) is utilized by each navigation system of each munition for determining an estimated position and covariance of the estimated position for each respective munition in the munition constellation.

4. The method for constraining navigational drift in a munition as recited in claim 1 , wherein Two-Way Timing and Ranging (TWTR) techniques are utilized by the navigation system of each munition to determine positioning of each munition relative to one another.

5. The method for constraining navigational drift in a munition as recited in claim 1 , wherein determining a relative position of each munition relative to the other munitions in the constellation via each munitions' datalink communication system further includes synchronizing an internal clock of each munition relative to at least one other munition in the munition constellation.

6. The method for constraining navigational drift in a munition as recited in claim 1 , wherein the estimated position and range is shared with each of the plurality of munitions in the munition constellation.

7. The method for constraining navigational drift in a munition as recited in claim 6 , wherein determining navigational drift for each munition via each munitions' navigation system utilizes the estimated position of each of the plurality of munitions and the range to each of the plurality of munitions in the munition constellation.

8. The method for constraining navigational drift in a munition as recited in claim 6 , wherein each munition in the munition constellation includes a seeker component for recognizing a ground target.

9. The method for constraining navigational drift in a munition as recited in claim 1 , wherein each munition in the munition constellation is preloaded with a flight plan to a predetermined target seeker basket.

10. The method for constraining navigational drift in a munition as recited in claim 1 , wherein each munition in the munition constellation is selected from the group consisting of: gun launched munitions; rocket propelled munitions; motor propelled munitions; air dropped munitions and Unmanned Aerial Vehicles.

11. A system for constraining navigational drift in a munition caused by Inertial Measurement Unit (IMU) bias error during flight of the munition in a constellation of a plurality of munitions in a Global Positioning System (GPS) denied attack of a plurality of ground targets, comprising:
a datalink communication system configured and operable to communicate with other munitions;
a navigation system for navigating the munition in flight, wherein the navigation system is communicatively coupled to the datalink communication system, the navigation system having a memory configured to store instructions in a processor disposed in communication with the memory, wherein the processor upon execution of the instructions is configured to:
determine an estimated position and covariance of the estimated position of the munition via the guidance system;
determine a range of the munition relative to at least one other munition in the munition constellation via the datalink communication system;
share the estimated position and range with the at least one other munition in the munition constellation by the datalink communication system;
determine navigational drift by the guidance system utilizing the estimated position of at least one other munition and the range to that at least one other munition in the munition constellation; and
constrain navigation drift of the munition by compensating for IMU bias error utilizing the determined navigational drift for the munition.

12. The system for constraining navigational drift as recited in claim 11 , wherein either an Extended Kalman Filter (EKF) or Unscented Kalman Filter (UKF) is utilized for determining an estimated position and covariance of the estimated position for each respective munition in the munition constellation.

13. The system for constraining navigational drift as recited in claim 11 , wherein Two-Way Timing and Ranging (TWTR) techniques are utilized by the navigation system to determine positioning of the munition relative to at least one other munition in the munition constellation.

14. The system for constraining navigational drift as recited in claim 11 , wherein determining a relative position relative to at least one other munition in the munition constellation further includes synchronizing an internal clock of each munition navigation system relative to at least one other munition in the munition constellation.

15. The system for constraining navigational drift as recited in claim 11 , wherein the estimated position and range is shared with each of the plurality of munitions in the munition constellation.

16. The system for constraining navigational drift as recited in claim 15 , wherein determining navigational drift for the munition utilizes the estimated position of each of the plurality of munitions and the range to each of the plurality of munitions in the munition constellation.

17. The system for constraining navigational drift as recited in claim 11 , wherein the munition further includes a seeker component for recognizing a ground target, wherein the seeker component is communicatively coupled to the guidance system.

18. The system for constraining navigational drift as recited in claim 11 , wherein each munition in the munition constellation is preloaded with a flight plan to a predetermined target seeker basket.

19. The system for constraining navigational drift as recited in claim 11 , wherein the munition is selected from the group consisting of: gun launched munitions; rocket propelled munitions; motor propelled munitions; air dr

Assignees

• Rosemount Aerospace Inc

Inventors

• Squillace Guy
• Willenbring Gary
• Ell Todd A

Classifications

• F41G7/36 Primary

  using inertial references · CPC title

• F41G7/2253

  Passive homing systems, i.e. comprising a receiver and do not requiring an active illumination of the target · CPC title

• G05D1/107

  specially adapted for missiles · CPC title

• F41G7/2233

  Multimissile systems · CPC title

• F41G7/008

  Combinations of different guidance systems · CPC title