Adaptive gain and phase controller for autopilot for a hypersonic vehicle

• US 5,102,072 A
• Filed: 11/19/1990
• Issued: 04/07/1992
• Est. Priority Date: 11/19/1990
• Status: Expired due to Term

• Current Assignee: Raytheon Company (Rtx Corporation)
• Original Assignee: General Dynamics Corporation
• Inventors: Egan, Murray C., Steketee, Frank D.
• Primary Examiner(s): Basinger, Sherman
• Assistant Examiner(s): MARQUIS, LISSI MOJICA
• Application Number:
  US07/617,250
• Time in Patent Office: 505 Days
• Field of Search: 364/433, 364/434, 244/3.2, 244/3.21, 244/175, 244/177, 244/178, 244/181, 244/191, 244/194, 244/195, 73/583, 318/584, 318/585, 318/586
• US Class Current: 244/195
• CPC Class Codes: G05D 1/0825 using mathematical models

Abstract

An adaptive gain and phase controller for an autopilot for a flight vehicle, such as a hypersonic glide vehicle, that includes applying a reference excitation signal to the control system of a flight vehicle, measuring the response of the vehicle to that excitation signal, namely the gain and phase losses through airframe, and making adjustments to the gain and phase inputs to the autopilot based on those measurements. A high gain narrow bandpass filter is incorporated so that the test signal can be extracted from the airframe of the flight vehicle.

Claims

1. An adaptive gain controller for a flight control system for a hypersonic vehicle which comprises:

a reference excitation signal generated within said hypersonic vehicle;

means for applying said reference excitation signal to the airframe of a hypersonic vehicle;

means to sense the response from the airframe to the reference excitation signal;

computer means coupled to the sensing means and adapted to utilize the responsive signal to compute a closed loop gain signal and a closed loop phase signal; and

autopilot means coupled to the computer means and adapted to used said closed loop gain and phase signals for real time flight control of said hypersonic vehicle.

2. The adaptive gain and phase controller for an autopilot for a hypersonic vehicle of claim 1 wherein the reference excitation signal is applied to at least one control surface of the hypersonic vehicle.

3. The adaptive gain and phase controller of claim 2 wherein the reference excitation signal is a sinusoidal dither signal having a predetermined frequency and amplitude.

4. The adaptive gain and phase controller of claim 1 wherein the means to sense the response from the airframe to the reference excitation signal includes an inertial measurement unit.

5. The adaptive gain and phase controller of claim 3 wherein the control surface of the vehicle is an elevator that is perturbed by the dither signal to cause a corresponding motion of the vehicle.

6. The adaptive gain and phase controller of claim 4 wherein the inertial measurement unit senses the pitch attitude and the flight path angle as a computed approximation of the angle of attack of the vehicle.

7. The adaptive gain and phase controller of claim 1 which further includes a filter means that is coupled to the sensing means and matched to the dither frequency to thereby extract the dither component of the signal from the coupled angle of attack.

8. The adaptive gain and phase controller of claim 7 wherein the filter means is a narrow band pass filter and the frequency of the excitation dither signal is selected so as to elicit a motion in the airframe of the hypersonic vehicle that can be sensed only be the dither filter.

9. The adaptive gain and phase controller of claim 7 wherein the computing means utilizes the computed approximate angle to determine the actual closed loop gain and closed loop phase which are the compared with the desired closed loop gain and closed loop phase to generate the error difference therebetween, which differences are then used to compute new gain and phase signals for application to the autopilot means.

10. The adaptive gain and phase controller of claim 6 wherein the computer means integrates the computed approximate angle of attack over half of the period of the excitation dither signal and compares the result with amplitude and phase of the excitation dither signal to determine the actual closed loop gain and closed loop phase.

11. The adaptive gain and phase controller of claim 10 wherein the computing means utilizes the actual closed loop gain and closed loop phase in a comparison with the desired gain and phase to determine the error difference therebetween, which differences are then used to compute new gain and phase control inputs to the autopilot means.

12. The adaptive gain and phase controller of claim 11 which further includes a clamp means which precludes the new gain and phase control signals from exceeding certain predetermined limits.

13. The adaptive gain and phase controller of claim 12 which further includes a second clamp means that disenables the generation of new gain and phase signals when large step commands have been added to the dither excitation signal.

14. A method of providing an adaptive gain and phase control for a flight control system for a hypersonic vehicle which comprises the steps of:

providing a reference excitation signal generated within said hypersonic vehicle;

applying said reference excitation signal to the airframe of said hypersonic vehicle;

sensing the response from the air frame to the reference excitation signal;

using the response signal to compute a closed loop gain and a closed loop phase signal; and

coupling the closed loop gain signal and the closed loop phase signal to the autopilot of the hypersonic vehicle to provide real time flight control of said vehicle.

15. The method of claim 14 wherein the reference excitation signal is a sinusoidal dither signal having a predetermined frequency and amplitude.

16. The method of claim 15 wherein the reference excitation signal is used to perturb at least one control surface of the hypersonic vehicle to cause a resultant responsive motion of the vehicle.

17. The method of claim 16 wherein the response to the reference excitation signal is sensed as the pitch attitude and the flight angle path of the vehicle by an inertial measurement unit as a computed approximation of the angle of attack of the vehicle.

18. The method of claim 17 wherein the computing step includes utilizing the computed approximate angle of attack to determine the actual closed loop gain and the closed loop phase which are then compared with the desired closed loop gain and closed loop phase to generate the error difference therebetween and using such differences to compute new gain and phase signals for application to the autopilot.

19. The method of claim 18 wherein the computing step includes integrating the computed approximated angle of attack over half of the period of the excitation dither signal and comparing the result with amplitude and phase of the excitation dither signal to determine the actual closed loop gain and closed loop phase.

20. The method of claim 19 wherein the computing step also includes precluding the new gain and phase signals from exceeding certain predetermined limits.