Method, apparatus and design procedure for controlling multi-input, multi-output (MIMO) parameter dependent systems using feedback LTI'zation

• US 6,859,689 B2
• Filed: 01/27/2003
• Issued: 02/22/2005
• Est. Priority Date: 05/30/2000
• Status: Expired due to Term

• Current Assignee: Rockwell Collins Control Technologies, Inc. (Rtx Corporation)
• Original Assignee: Athena Technologies (Rtx Corporation)
• Inventors: Vos, David W.
• Primary Examiner(s): Nguyen, Tan Q.
• Assistant Examiner(s): Tran, Dalena
• Application Number:
  US10/351,436
• Publication Number:
  US 20030191561A1
• Time in Patent Office: 757 Days
• Field of Search: 701/3, 701/4, 701/11, 701/14, 701/15, 701/18, 244/196, 244/181, 244/182, 244/177, 244/3.21, 244/17.3, 244/76.R, 708/5, 708/6, 708/801
• US Class Current: 701/4
• CPC Class Codes: G05B 11/32 with inputs from more than one sensing element; with outputs to more than one correcting element
• CPC Class Codes: G05B 13/042 in which a parameter or coefficient is automatically adjusted to optimise the performance
• CPC Class Codes: G05B 9/02 electric
• CPC Class Codes: G05B 9/03 with multiple-channel loop, i.e. redundant control systems
• CPC Class Codes: G05D 1/0825 using mathematical models

Abstract

A method and apparatus are provided for controlling a dynamic device having multi-inputs and operating in an environment having multiple operating parameters. A method of designing flight control laws using multi-input, multi-output feedback LTI'"'"'zation is also provided. The method includes steps of: (i) determining coordinates for flight vehicle equations of motion; (ii) transforming the coordinates for the flight vehicle equations of motion into a multi-input linear time invariant system; (iii) establishing control laws yielding the transformed equations of motion LTI; (iv) adjusting the control laws to obtain a desired closed loop behavior for the controlled system; and (v) converting the transformed coordinates control laws to physical coordinates.

Claims

1. A method of determining the operational status of a multi-input, multi-parameter dependent control system for controlling a dynamic device, said method comprising the steps of:

receiving a plurality of current status signals representing current statuses of the device and a plurality of control signals for effecting control of the device;

transforming the current status signals and the control signals to a multi-input linear time invariant system;

estimating an expected behavior of the device using the transformed current status signals and the transformed control signals; and

determining the operational status of the control system by comparing the expected behavior of the device to the actual behavior of the device.

2. The method of claim 1, further comprising the steps of:

incrementally adjusting at least one parameter based on the determined operational status of the control system; and

updating the determination of the operational status by repeating the receiving, transforming, estimating, and determining steps.

3. The method of claim 2, wherein characteristics of the dynamic device are definable by at least one control law, and wherein the step of incrementally adjusting comprises the steps of:

generating at least one parameter rate of change term; and

applying the at least one parameter rate of change term to the at least one control law.

4. The method of claim 3, wherein the generating step is performed using linear interpolation.

5. The method of claim 3, wherein the generating step is performed using extrapolation techniques.

6. The method at claim 3, wherein the generating step is performed using curve fitting.

7. The method of claim 2, wherein the dynamic device comprises a flight vehicle, and wherein the plurality of status signals includes at least one of the group consisting of an airspeed signal, an altimeter signal, a yaw rate signal, a bank angle signal, a side slip signal, an angle of attack signal, a pitch rate signal, a pitch attitude signal, and a roll rate signal.

8. The method of claim 7, wherein the at least one parameter corresponds to at least one of the group consisting of a throttle, an elevator, an aileron, and a rudder, and the step of incrementally adjusting comprises using an actuator to physically adjust at least one of the group consisting of a throttle, an elevator, an aileron, and a rudder.

9. The method of claim 7, wherein the flight vehicle is unmanned.

10. The method of claim 2, wherein the steps of incrementally adjusting and repeating are performed at predetermined time intervals.

11. A multi-parameter dependent control system for controlling a dynamic device having multiple inputs, said system comprising:

receiving means for receiving a plurality of current state signals representing current states of the device and a plurality of control signals for effecting control of the device;

transforming means for transforming the current state signals and the control signals to a linear time invariant system;

estimating means for estimating an expected behavior of the device using the transformed current state signals and the transformed control signals and for generating estimate signals corresponding to the expected behavior, and

determining means for determining the operational status of the control system by comparing the expected behavior of the device to the actual behavior of the device.

12. The system of claim 11, further comprising:

adjusting means for incrementally adjusting at least one parameter based on the determined operational status of the control system, wherein

the determining means is further configured to update the determination of the operational status by repeating a use of the receiving means, transforming means, estimating means, and determining means when an incremental adjustment has been made.

13. The system of claim 12, wherein characteristics of the dynamic device are definable by at least one control law, and wherein the adjusting means is further configured to:

generate at least one parameter rate of change term; and

apply the at least one parameter rate of change term to the at least one control law.

14. The system of claim 13, wherein the adjusting means is further configured to generate the at least one parameter rate of change term by using linear interpolation.

15. The system of claim 13, wherein the adjusting means is further configured to generate the at least one parameter rate of change term by using extrapolation techniques.

16. The system of claim 13, wherein the adjusting means is further configured to generate the at least one parameter rate of change term by using curve fitting.

17. The system of claim 12, wherein the dynamic device comprises a flight vehicle, and wherein the plurality of current state signals includes at least one of the group consisting of an airspeed signal, an altimeter signal, a yaw rate signal, a bank angle signal, a side slip signal, an angle of attack signal, a pitch rate signal, a pitch attitude signal, and a roll rate signal.

18. The system of claim 17, wherein the at least one parameter corresponds to at least one of the group consisting of a throttle, an elevator, an aileron, and a rudder, and wherein the adjusting means is further configured to use an actuator to physically adjust at least one of the group consisting of a throttle, an elevator, an aileron, and a rudder.

19. The system of claim 17, wherein the flight vehicle is unmanned.

20. The system of claim 12, wherein the adjusting means is further configured to make an incremental adjustment at predetermined time intervals.

21. Apparatus for detecting a failure in a flight control device having multiple inputs and operating in an environment having multiple parameters, comprising:

processing structure for (i) receiving time-varying status signals from the flight control device, (ii) providing reference signals corresponding to the flight control device, (iii) transforming both the status signals and the reference signals to a linear time invariant coordinate system, (iv) calculating flight control device estimate signals based on the transformed status signals and the transformed reference signals, (v) transforming the calculated estimate signal in a physical coordinate system, and (vi) detecting an error in the flight control device when a difference between the transformed estimate signals and the status signals exceed a predetermined threshold.

22. The apparatus of claim 21, wherein the time-varying status signals include at least one of the group consisting of an airspeed signal, an altimeter signal, a yaw rate signal, a bank angle signal, a side slip signal, an angle of attack signal, a pitch rate signal, a pitch attitude signal, and a roll rate signal.

23. The apparatus of claim 21, wherein the processing structure is further configured to calculate flight control estimate signals using at least one control law.

24. The apparatus of claim 21, wherein the processing structure is further configured to update the calculated flight control device estimate signals at predetermined time intervals.

25. The apparatus of claim 21, wherein the flight control device is unmanned.