Non-linear compensation of a control system having an actuator and a method therefore

• US 20040078120A1
• Filed: 10/16/2002
• Published: 04/22/2004
• Est. Priority Date: 10/16/2002
• Status: Active Application

• Current Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Original Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Inventors: Melkers, Edgar, Sahasrabudhe, Vineet
• Application Number:
  US10/271,466
• Publication Number:
  US 20040078120A1
• Time in Patent Office: Days
• US Class Current: 701/3
• CPC Class Codes: G05B 13/021 in which a variable is automatically adjusted to optimise the performance
• CPC Class Codes: G05B 17/02 electric

Abstract

A control system compensation algorithm which operates as a comparator of a nominal state and unlimited dynamic state of an actuator. Upon reaching either rate or position saturation, the difference between the nominal state actuator model and the unlimited dynamics actuator model is the excess command signal of an uncompensated actuator command which would put the actuator into saturation. The excess command is then filtered to the designed system bandwidth. The filtered excess servo command from filter is then subtracted from the original uncompensated actuator command signal to generate the rate limited actuator command.

Claims

1. A control system comprising

a nominal state actuator model of an actuator, said nominal state actuator model in communication with an uncompensated actuator command;

an unlimited dynamics actuator model of said actuator, said unlimited dynamics actuator model in communication with said uncompensated actuator command; and

a filter communicating with said nominal state actuator model and said unlimited dynamics actuator model to filter a difference therebetween to generate a filtered difference and add said filtered difference to said uncompensated actuator command to generate a rate limited actuator command.

2. The control system as recited in claim 1, further comprising a degraded state actuator model in communication with said uncompensated actuator command.

3. The control system as recited in claim 2, further comprising a selection circuit which selects between said nominal state actuator model and said degraded state actuator model.

4. The control system as recited in claim 3, wherein said selection circuit selects between said nominal state actuator model and said degraded state actuator model in response to a measured output of said actuator.

5. The control system as recited in claim 3, wherein said selection circuit selects between said nominal state actuator model and said degraded state actuator model in response to a measured output of a control surface.

6. The control system as recited in claim 1, wherein said actuator comprises a flight control actuator.

7. The control system as recited in claim 1, further comprising a flight control processor which generates said uncompensated actuator command.

8. A method of controlling an actuator comprising the steps of:

(1) modeling a nominal state of the actuator;

(2) modeling an unlimited dynamic state of the actuator; and

(3) filtering a difference between said step (1) and said step (2) for an uncompensated actuator command; and

(4) summing the filtered difference from said step (3) with the uncompensated actuator command to generate a rate limited actuator command.

9. A method as recited in claim 8, wherein said step (1) further comprises a nominal rate limit of the actuator.

10. A method as recited in claim 9, further comprising the step of:

estimating the nominal rate limit in response to a present actuator condition.

11. A method as recited in claim 8, wherein said step (1) further comprises a nominal position limit of the actuator.

12. A method as recited in claim 11, further comprising the step of estimating the nominal position limit in response to a present actuator condition.

13. A method as recited in claim 8, wherein said step (3) further comprises filtering a high frequency component of the difference between said step (1) and said step (2).

14. A method as recited in claim 8, wherein said step (3) further comprises filtering the difference between said step (1) and said step (2) to a predetermined system bandwidth.

15. A method as recited in claim 8, further comprising the steps of:

(a) modeling a degraded state of the actuator; and

(b) selecting between the nominal state actuator model and the degraded state actuator model in response to a measured output of the actuator.

16. A method as recited in claim 8, further comprising the steps of:

(a) driving the actuator in response to the rate limited actuator command;

(b) operating a flight control surface with the actuator.

17. A method of controlling a flight control system actuator comprising the steps of:

(1) modeling a nominal state of the actuator;

(2) modeling an unlimited dynamic state of the actuator; and

(3) filtering a difference between said step (1) and said step (2); and

(4) summing the filtered difference from said step (3) with the uncompensated actuator command to generate a rate limited actuator command.

18. A method as recited in claim 17, further comprising the steps of:

(a) modeling a degraded state of the actuator; and

(b) selecting between the nominal state actuator model and the degraded state actuator model in response to a measured output of the actuator.

19. A method as recited in claim 17, further comprising the steps of:

(a) driving the actuator in response to the rate limited actuator command; and

(b) operating a flight control surface with the actuator.

20. A computer readable storage medium containing a plurality of executable instructions for controlling an actuator, comprising:

a first set of instructions directing the computer to model a nominal state of the actuator;

a second set of instructions directing the computer to model an unlimited dynamic state of the actuator;

a third set of instructions directing the computer to filter a difference between the nominal state of the actuator and the unlimited dynamic state of the actuator for an uncompensated actuator command; and

a fourth set of instructions directing the computer to sum the filtered difference between the nominal state of the actuator and the unlimited dynamic state of the actuator for the uncompensated actuator command with the uncompensated actuator command to generate a rate limited actuator command.

21. The storage medium of claim 20, further comprising instructions directing the computer to model a degraded state of the actuator.

22. The storage medium of claim 21, further comprising instructions directing the computer to select between the nominal state actuator model and the degraded state actuator model in response to a measured output of the actuator