Dynamic autopilot

Patent metadata

Field	Value
Publication number	US-11480413-B2
Application number	US-201716604011-A
Country	US
Kind code	B2
Filing date	Apr 10, 2017
Priority date	Apr 10, 2017
Publication date	Oct 25, 2022
Grant date	Oct 25, 2022

Abstract

[A system and method for dynamic autopilot control comprising providing input to a guidance and control autopilot comprising Mach and dynamic pressure; tailoring parameters of the autopilot, the parameters comprising: roll gain; a pitch/yaw gain; a pitch/yaw loop compensator frequency; a guidance filter bandwidth; a guidance filter lead compensator frequency; and a navigation gain.

First claim

What is claimed is:

1. A method for dynamic autopilot control of a projectile, comprising:
obtaining sensor data from at least one on-board sensor, wherein said at least one sensor comprises an accelerometer, a temperature sensor, and a pressure sensor;
providing said sensor data to at least one processor coupled to said dynamic autopilot, wherein said processor calculates at least one of Mach and dynamic pressure;
tailoring parameters of said dynamic autopilot, said dynamic autopilot parameters comprising at least one of:
a roll control filter parameters;
a pitch/yaw filter parameters;
a guidance filter parameters; and
filtering pitch/yaw data with a pitch/yaw loop compensator such effects of coupling instabilities between pitch and yaw channels are reduced;
guiding said projectile to a target using said dynamic autopilot control.

2. The method of claim 1 , wherein said roll control filter parameters comprise a roll gain schedule.

3. The method of claim 1 , wherein said pitch/yaw filter parameters comprise a pitch/yaw gain schedule.

4. The method of claim 1 , wherein said pitch/yaw filter parameters comprise a pitch/yaw loop compensator frequency.

5. The method of claim 1 , wherein said guidance filter parameters comprise a guidance filter bandwidth.

6. The method of claim 1 , wherein said guidance filter parameters comprise a lead compensator frequency.

7. The method of claim 1 , wherein said dynamic autopilot parameters comprise a navigation gain.

8. The method of claim 1 , wherein roll and pitch/yaw innermost control loops are rate loops.

9. The method of claim 1 , wherein said dynamic autopilot parameters comprise further control loops that depend on airframe transfer functions.

10. The method of claim 9 , wherein said further control loops comprise attitude loops.

11. The method of claim 9 , wherein said further control loops comprise acceleration loops.

12. The method of claim 9 , wherein said further control loops comprise proportional-navigation guidance loops.

13. The method of claim 9 , wherein said further control loops comprise augmented proportional-navigation guidance loops.

14. The method of claim 1 , comprising airframe transfer functions comprising aerodynamic control derivatives (Cldr(M) and Cmdp(M)) and dynamic pressure (q).

15. A system for dynamic autopilot control of a projectile to a target, comprising:
a guidance and control autopilot;
at least one on-board sensor, wherein said at least one on-board sensor comprises an accelerometer, a temperature sensor, and a pressure sensor;
at least one processor executing a program performing as follows:
processing a Mach and a dynamic pressure;
deriving parameters for said dynamic autopilot, said parameters comprising:
a roll gain;
a pitch/yaw gain;
a pitch/yaw loop compensator frequency;
a guidance filter comprising a guidance filter bandwidth and a guidance filter lead compensator frequency; and
a navigation gain;

wherein said dynamic autopilot guides said projectile to said target; and
wherein a pitch/yaw loop compensator comprises at least one of a filter component that reduces effects of coupling instabilities between pitch and yaw channels or a filter component with a corner frequency related to a flight path pole wherein it is scaled by dynamic pressure.

16. The system of claim 15 , wherein said roll gain is retrieved from a lookup table and scaled with measured dynamic pressure.

17. The system of claim 15 , wherein at higher platform speeds associated with fixed wing platforms, said roll gain is inversely scaled with dynamic pressure whereby higher dynamic pressure and Mach sensitivity of aerodynamic control derivatives are accommodated.

18. A non-transitory computer-readable medium for dynamic autopilot control of a projectile, comprising instructions stored thereon, that when executed on at least one processor, perform the steps of:
providing input to a guidance and control autopilot;
said input comprising Mach and dynamic pressure;
tailoring parameters of said autopilot, said parameters comprising:
a roll gain;
a pitch/yaw gain;
a pitch/yaw loop compensator frequency;
a guidance filter comprising a guidance filter bandwidth and a guidance filter lead compensator frequency;
a navigation gain;
wherein at higher platform speeds associated with fixed wing platforms, roll gains are inversely scaled with dynamic pressure whereby higher dynamic pressure and Mach sensitivity of aerodynamic control derivatives are accommodated;
wherein a pitch/yaw loop compensator comprises a filter component with a corner frequency related to a flight path pole whereby it is scaled by dynamic pressure; and
guiding said projectile to a target using said dynamic autopilot control.

Assignees

• Bae Sys Inf & Elect Sys Integ

Inventors

• Schorr David J
• Batchelder Jason H
• Gibson Jeremy B
• Steenson Jr James H

Classifications

• G05D1/12

  Target-seeking control · CPC title

• F42B10/60

  Steering arrangements (F42B19/01 takes precedence) · CPC title

• F41G7/36 Primary

  using inertial references · CPC title