Gimbal over rate prevention system and method

• US 9,561,873 B2
• Filed: 02/20/2014
• Issued: 02/07/2017
• Est. Priority Date: 02/20/2014
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Dominguez, Jose
• Primary Examiner(s): Jabr, Fadey
• Assistant Examiner(s): Soofi, Yazan A
• Application Number:
  US14/185,303
• Publication Number:
  US 20150232203A1
• Time in Patent Office: 1,083 Days
• Field of Search: 701/13
• US Class Current: 1/1
• CPC Class Codes: B64G 1/244 Spacecraft control systems
• CPC Class Codes: B64G 1/286 using control momentum gyroscopes (CMGs)
• CPC Class Codes: B64G 1/36 using sensors, e.g. sun-sensors, horizon sensors
• CPC Class Codes: Y10T 74/1229 Gyroscope control

Abstract

A system and method for preventing a gimbal from exceeding a predetermined gimbal rate limit includes receiving a gimbal rate command and a gimbal rate feedback signal representative of sensed gimbal rate. The gimbal rate command and the gimbal rate feedback signal are compared, in a control circuit, to determine a gimbal rate error. A predetermined gain scaling factor is applied, in the control circuit, to the gimbal rate command to generate a scaled gimbal rate command. The gimbal is disabled when the gimbal rate error is greater than or equal to the scaled gimbal rate.

Claims

1. A method for preventing a gimbal from exceeding a predetermined gimbal rate limit, comprising the steps of:

receiving a gimbal rate command;

receiving a gimbal rate feedback signal representative of sensed gimbal rate;

comparing, in a control circuit, the gimbal rate command and the gimbal rate feedback signal to determine a gimbal rate error;

applying, in the control circuit, a predetermined gain scaling factor to the gimbal rate command to generate a scaled gimbal rate command; and

disabling the gimbal when the gimbal rate error is greater than or equal to the scaled gimbal rate command.

2. The method of claim 1, further comprising:

filtering the gimbal rate command in a low-pass filter after receiving the gimbal rate command.

3. The method of claim 1, wherein the disabling step comprises:

de-energizing a gimbal motor that is coupled to the gimbal.

4. The method of claim 1, further comprising:

applying, in the control circuit, a first absolute value function to the gimbal rate error to obtain a gimbal rate error magnitude; and

applying, in the control circuit, a second absolute value function to the scaled gimbal rate command to obtain a scaled gimbal rate command magnitude.

5. The method of claim 4, wherein the disabling step comprises:

disabling the gimbal when the gimbal rate error magnitude is greater than or equal to the scaled gimbal rate command magnitude.

6. A control moment gyro (CMG), comprising:

a gimbal configured to rotate about a gimbal axis;

a CMG rotor rotationally coupled to the gimbal and configured to rotate about a spin axis that is perpendicular to the gimbal axis;

a gimbal motor coupled to the gimbal, the gimbal motor adapted to be selectively energized and configured, upon being energized, to rotate the gimbal at a gimbal rate about the gimbal axis;

a rate sensor configured to sense the gimbal rate and supply a gimbal rate feedback signals representative of sensed gimbal rate; and

a gimbal control coupled to receive gimbal rate commands and the gimbal rate feedback signals, the gimbal control configured, upon receipt of the gimbal rate commands and the gimbal rate feedback signals, to (i) compare the gimbal rate commands and the gimbal rate feedback signals to determine a gimbal rate error magnitude, (ii) apply a predetermined gain scaling factor to the gimbal rate command to generate a scaled gimbal rate command, and (iii) de-energize the gimbal motor when the gimbal rate error magnitude is greater than or equal to the scaled gimbal rate command.

7. The CMG of claim 6, wherein the gimbal control further comprises:

a low-pass filter coupled to receive the gimbal rate commands and, configured, upon receipt thereof, to supply delayed gimbal rate commands.

8. The CMG of claim 6, wherein the gimbal control is further configured to:

apply a first absolute value function to the gimbal rate error to obtain a gimbal rate error magnitude; and

apply a second absolute value function to the scaled gimbal rate command to obtain a scaled gimbal rate command magnitude.

9. The CMG of claim 8, wherein the gimbal control is configured to de-energize the gimbal motor when the gimbal rate error magnitude is greater than or equal to the scaled gimbal rate command magnitude.

10. An attitude control system, comprising:

an attitude control configured to selectively supply the gimbal rate commands; and

a control moment gyro (CMG) configured to rotate about a gimbal axis, the CMG coupled to receive the gimbal rate commands and configured, upon receipt thereof, to rotate at the commanded gimbal rate about the gimbal axis, the CMG comprising;

a rate sensor configured to sense gimbal rate and supply a gimbal rate feedback signals representative of sensed gimbal rate; and

a gimbal control coupled to receive the gimbal rate commands and the gimbal rate feedback signals, the gimbal control configured, upon receipt of the gimbal rate commands and the gimbal rate feedback signals, to (i) compare the gimbal rate commands and the gimbal rate feedback signals to determine a gimbal rate error magnitude, (ii) apply a predetermined gain scaling factor to the gimbal rate command to generate a scaled gimbal rate command, and (iii) supply a gimbal disable signal when the gimbal rate error magnitude is greater than or equal to the scaled gimbal rate command.

11. The system of claim 10, wherein the gimbal control further comprises:

a low-pass filter coupled to receive the gimbal rate commands and, configured, upon receipt thereof, to supply delayed gimbal rate commands.

12. The system of claim 10, wherein the gimbal control is further configured to:

apply a first absolute value function to the gimbal rate error to obtain a gimbal rate error magnitude; and

apply a second absolute value function to the scaled gimbal rate command to obtain a scaled gimbal rate command magnitude.

13. The system of claim 12, wherein the gimbal control is configured to de-energize the gimbal motor when the gimbal rate error magnitude is greater than or equal to the scaled gimbal rate command magnitude.