Non colocated rate sensing for control moment gyroscopes

• US 5,875,676 A
• Filed: 09/02/1997
• Issued: 03/02/1999
• Est. Priority Date: 09/02/1997
• Status: Expired due to Fees

• Current Assignee: Honeywell Incorporated (Honeywell International Inc.)
• Original Assignee: Honeywell Incorporated (Honeywell International Inc.)
• Inventors: Heiberg, Christopher J., Bailey, David A.
• Primary Examiner(s): Bonck, Rodney H.
• Application Number:
  US08/922,224
• Time in Patent Office: 546 Days
• Field of Search: 74/5.34, 74/5.4, 74/5.22, 74/5.6 R, 74/5.6 A, 244/165, 73/504.09
• US Class Current: 74/5.22
• 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 74/1218 Combined
• CPC Class Codes: Y10T 74/1221 Multiple gyroscopes
• CPC Class Codes: Y10T 74/1229 Gyroscope control

Abstract

A feedback system for use in controlling control moment gyroscopes that are used in positioning a spacecraft where the relative rate of rotation is determined from the difference between the rotation rate of the gimbals of the CMGs and the rotation rate of the frame about the gimbal axis. The inertial reference units on the spacecraft are utilized as the source of measured rates of rotation of the three spacecraft axes with respect to a predetermined axis and these are converted to the rates of rotation of the frame about the individual CMG gimbal axes.

Claims

1. In a control system including a control moment gyro having at least one gimbal and at least one gimbal axis and a sensor for producing a first signal indicative of the rate of rotation of the gimbal about the gimbal axis, the control moment gyro being mounted on a movable member to produce a torque which causes rotation of the movable member about a predetermined axis, the movable member including sensing means for producing a second signal indicative of the rate of rotation of the movable member about the predetermined axis, the improvement comprising:

transforming means connected to receive the second signal and to produce a third signal which is indicative of the rate of rotation of the movable member about the gimbal axis;

means connected to receive the first and third signals and operable to produce a fourth signal indicative of the relative rate of rotation between the rate rotation of the gimbal about the gimbal axis and the rate of rotation of the movable member about the gimbal axis; and

,

feedback means connecting the control moment gyro to receive the fourth signal and to produce the torque in accordance therewith.

2. The system according to claim 1 wherein the movable member is a spacecraft.

3. The system according to claim 2 wherein the sensor for producing the first signal is an absolute rate sensor.

4. The system according to claim 3 wherein the absolute rate sensor is a fiber optic gyro.

5. The system according to claim 1 further including means producing a fifth signal indicative of a desired rate of rotation of the movable member about the gimbal axis, and means comparing the fourth and fifth signals to produce a feedback signal, the feedback means connecting the control moment gyro to receive the fourth signal and to produce the torque in accordance therewith.

6. The system according to claim 5 wherein the sensing means produces a sixth signal indicative of the angle between the predetermined direction and a reference direction and further including:

means producing a seventh signal indicative of a desired angle between the predetermined direction and the reference direction; and

a controller connected to receive the sixth and seventh signals and operable to produce the fifth signal in accordance therewith.

7. The system according to claim 1 further including second and third control moment gyros each having a gimbal and a gimbal axis and a sensor for producing additional first signals indicative of the rate of rotation of the gimbal about the gimbal axis of the second and third control moment gyros respectively, the second and third control moment gyros being mounted on a movable member to produce a second and third torques which causes rotation of the movable member about second and third predetermined axes respectively, the movable member including sensing means for producing further second signals indicative of the rate of rotation of the movable member about the second and third predetermined axes respectively, and wherein the transforming means is connected to receive the further second signals and to produce further third signals indicative of the rate of rotation of the movable member about the gimbal axes of the second and third control moment gyros and wherein further fourth signals indicative of the relative rate of rotation between the rate rotation of the gimbal about the gimbal axes of the second and third control moment gyros and the rate of rotation of the movable member about the gimbal axes of the second and third control moment gyros are produced and the feedback means connects the second and third control moment gyros to receive the further fourth signals and to produce the second and third torques in accordance therewith.

8. The system according to claim 7 wherein the movable member is a spacecraft.

9. The system according to claim 8 wherein the sensors for producing the first signals are absolute rate sensors.

10. The system according to claim 9 wherein the absolute rate sensors are fiber optic gyros.

11. Apparatus for controlling movement of a spacecraft having inertial sensors which produce a first, second and third signals, each indicative of the rate of rotation of the craft about one of first, second and third axes respectively:

first, second and third control moment gyros, each having a gimbal frame mounted to the spacecraft, having a gimbal assembly mounted on the gimbal frame for rotation about a gimbal axis, and being operable in accordance with an input signal to produce a torque causing rotation of the spacecraft about one of the first, second and axes;

first, second and third sensing means operable to produce a fourth, fifth and sixth signals each indicative of the rate of rotation of the gimbal assembly of one of the first second and third control moment gyros about the gimbal axis thereof, transformation means connected to receive the first, second and third signals and to produce seventh, eighth and ninth signals, each indicative of the rate of rotation of the spacecraft about the gimbal axis of one of the first, second and third control moment gyros respectively;

first, second and third difference means each connected to receive one of the fourth, fifth and sixth signals and one of the seventh, eighth and ninth third signals respectively for producing tenth, eleventh and twelfth signals, each indicative of the difference between the rate of rotation of the gimbal assembly about the gimbal axis of one of the first, second and third control moment gyros and the rate of rotation of the spacecraft about the gimbal axis of one of the first second and third control moment gyros respectively; and

feedback means connecting the each of the first, second and third control moment gyros to receive one of the tenth, eleventh and twelfth signals respectively for use in producing the first, second and third torques respectively.

12. The apparatus of claim 11 wherein the inertial sensors are laser angular rate sensors.

13. The apparatus of claim 11 wherein the spacecraft sensors further produce signals indicative of the angles between the first second and third predetermined axes and a reference axis and further including controller means receiving the signals indicative of the angles and receiving signals indicative of desired angles, the controller means operable to produce signals indicative of desired rates of rotation of the space craft about the gimbal axes of the first, second and third axes respectively and comparing means receiving the signals indicative of the desired rates and receiving the tenth eleventh and twelfth signal to produce first, second and third feedback signals, and wherein the feedback means connects each of the first, second and third control moment gyros to receive one of the first second and third feedback signals respectively for use in producing the first, second and third torques respectively.

14. The method of controlling the rate of rotation of a space craft about a predetermined axis which spacecraft includes inertial sensors operable to produce first signals indicative of the rate of rotation of the space craft about the inertial axes thereof and which utilizes control moment gyros to produce torque about the predetermined axis, comprising the steps of

A. producing second signals indicative of the rate of rotation of the gimbals of the control moment gyros about the gimbal axes thereof;

B. producing third signals from the first signals, the third signals indicative of the rate of rotation of the spacecraft about the gimbal axes;

C. comparing the second and third signals to produce fourth signals indicative of the relative rate of rotation of the gimbals and the spacecraft about the gimbal axes;

D. comparing the fourth signals with fifth signals indicative of the desired relative rate of rotation of the gimbals and the spacecraft about the gimbal axes to produce feedback signals; and

E. providing the fifth signals to the control moment gyros to produce the torque.