Method for controlling a projectile with maneuver envelopes

Patent metadata

Field	Value
Publication number	US-11555680-B2
Application number	US-201917263960-A
Country	US
Kind code	B2
Filing date	Aug 30, 2019
Priority date	Aug 31, 2018
Publication date	Jan 17, 2023
Grant date	Jan 17, 2023

Abstract

A guided projectile including a precision guidance munition assembly utilizes at least one maneuver envelope to optimally control movement of at least one canard to steer the guided projectile during flight. The maneuver envelopes optimize movements of the at least one canard that effectuate movement in either the range direction or the cross-range direction, or both. The maneuver envelope enables optimal timing such that maneuvering in one direction does not come at the expense of maneuver authority in the other direction.

First claim

The invention claimed is:

1. A method, comprising:
selecting a maneuver envelope that describes a control authority of a guided projectile including a precision guidance munition assembly, wherein the selected maneuver envelope comprises a plurality of command rings at a plurality of time intervals indicating a range maneuverability and a cross-range maneuverability and the roll angles of the precision guidance munition assembly;
predicting an impact point of the guided projectile relative to a target;
determining a miss distance based on the predicted impact point relative to the target;
determining a maneuver command based on the selected maneuver envelope; and
applying the maneuver command to move at least one canard on a canard assembly at an optimal time based, at least in part, on the selected maneuver envelope.

2. The method of claim 1 , wherein the selected maneuver envelope is based, at least in part, on a launch velocity and a quadrant elevation of the guided projectile.

3. The method of claim 1 , wherein the maneuver envelope is selected from a plurality of maneuver envelopes stored in at least one non-transitory computer-readable storage medium.

4. The method of claim 1 , wherein the maneuver envelope is selected by loading a predetermined maneuver envelope to the at least one non-transitory computer-readable storage medium prior to firing the guided projectile.

5. The method of claim 1 , wherein the selected maneuver envelope comprises a plurality of command rings identifying an amount of a ground maneuver per second as a function of time.

6. The method of claim 5 , wherein the ground maneuver per second as a function of time is based, at least in part, on a roll angle and a maximum canard deflection.

7. The method of claim 6 , further comprising:
selecting the roll angle from a specific time interval of the selected maneuver envelope to reduce the miss distance.

8. The method of claim 6 , wherein the selected maneuver envelope specifies a range control reversal wherein when the maneuver command is applied within a first time interval the range increases when the maneuver command is applied within a second time interval the range decreases.

9. The method of claim 6 , wherein the roll angle that is required to reduce the miss distance depends on the time interval when the maneuver command is applied.

10. The method of claim 1 , wherein the plurality of command rings are determined through a modeling function accounting for the launch velocity and the quadrant elevation of the guided projectile.

11. The method of claim 1 , further comprising:
utilizing a canard logic to move the at least one canard in response to a signal from the at least one processor associated with the maneuver envelope.

12. The method of claim 1 , further comprising:
producing a dot product for a match ratio versus time; and
evaluating whether the maneuver command is effective.

13. The method of claim 12 , wherein the selected maneuver command is effective if the match ratio versus time is greater than or equal to approximately 0.85.

14. The method of claim 12 , further comprising:
preventing the selected maneuver command from being applied at an initial time based, at least in part, on the match ratio versus time.

15. The method of claim 14 , further comprising:
applying the selected maneuver command to move the at least one canard on the canard assembly at a subsequent time that is different than the initial time based, at least in part, on the match ratio versus time.

16. The method of claim 12 , wherein the instructions further comprise:
applying the selected maneuver command to move the at least one canard on the canard assembly based, at least in part, on the match ratio versus time.

17. The method of claim 12 , wherein the dot product includes normalized vectors.

18. The method of claim of claim 12 , further comprising:
preventing the selected maneuver command from being applied during a maneuverability dead zone.

19. A computer program product including one or more non-transitory machine-readable mediums having instructions encoded thereon that, when executed by one or more processors, result in a plurality of operations for guiding a projectile to a target, the operations comprising:
selecting a maneuver envelope that provides a control authority of the projectile, wherein the selected maneuver envelope comprises a plurality of command rings at a plurality of time intervals indicating a range maneuverability and a cross-range maneuverability and the roll angles of the precision guidance munition assembly;
predicting an impact point of the projectile relative to the target;
determining a miss distance based on the predicted impact point relative to the target;
determining a maneuver command based on the maneuver envelope; and
applying the maneuver command to move at least one canard of the projectile at an optimal time based, at least in part, on the maneuver envelope.

Assignees

• Bae Sys Inf & Elect Sys Integ

Inventors

• Zemany Paul
• Chrobak Matthew
• Degtiarev Egor V

Classifications

• F41G7/008

  Combinations of different guidance systems · CPC title

• 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

• F41G7/346

  using global navigation satellite systems, e.g. GPS, GALILEO, GLONASS · CPC title