Control moment gyroscope array and method of power distribution therefor

• US 8,210,062 B2
• Filed: 04/18/2007
• Issued: 07/03/2012
• Est. Priority Date: 04/18/2007
• Status: Expired due to Fees

• Current Assignee: Ithaco Space Systems, Inc. (Rtx Corporation)
• Original Assignee: Ithaco Space Systems, Inc. (Rtx Corporation)
• Inventors: Stromswold, Eric, Bialke, William Edward
• Primary Examiner(s): Le, David D
• Assistant Examiner(s): Scott, Jacob S
• Application Number:
  US11/787,967
• Publication Number:
  US 20100044517A1
• Time in Patent Office: 1,903 Days
• Field of Search: 74/54.7, 74/52.2
• US Class Current: 74/5.47
• CPC Class Codes: B64G 1/286 using control momentum gyroscopes (CMGs)
• CPC Class Codes: Y10T 74/1218 Combined
• CPC Class Codes: Y10T 74/1229 Gyroscope control
• CPC Class Codes: Y10T 74/1254 by motor torque

Abstract

An attitude control system for a spacecraft is disclosed that includes a scissored pair of control moment gyroscopes for delivering an output torque to the spacecraft along a an output axis, wherein each gyroscope has a spin motor for spinning a rotor about a rotor axis and a gimbal torque motor for rotating the rotor about a gimbal axis, and wherein the system includes a generator for extracting kinetic energy from the rotors during rotor deceleration to power the gimbal torque motors of the gyroscopes.

Claims

1. A directional control array for a spacecraft comprising:

a) a first control moment gyroscope having a first rotor, a first spin motor to spin the first rotor about a first rotor axis, and a first gimbal motor to rotate the first rotor about a first gimbal axis that is normal to the first rotor axis;

b) a first spin motor/generator driver adapted to extract stored kinetic energy from the first rotor as the first rotor is decelerated during a period of peak spacecraft torquing;

c) a first gimbal motor driver adapted to receive extracted energy delivered directly from the first spin motor/generator driver to power the first gimbal motor;

d) a second control moment gyroscope having a second rotor, a second spin motor to spin the second rotor about a second rotor axis, a second gimbal motor to rotate the second rotor about a second gimbal axis that is normal to the second rotor axis;

e) a second spin motor/generator driver adapted to extract stored kinetic energy from the second rotor as the second rotor is decelerated during said period of peak spacecraft torquing; and

f) a second gimbal motor driver adapted to receive extracted energy delivered directly from the second spin motor/generator driver to power the second gimbal motor.

2. A directional control array as recited in claim 1, wherein the first and second control moment gyroscopes have parallel gimbal axes.

3. A directional control array as recited in claim 1, further comprising means for controlling gimbal angle and gimbal rate of the first and second gimbal motors.

4. An attitude control system for a spacecraft comprising:

a) a first scissored pair of control moment gyroscopes for delivering an output torque to the spacecraft along a first output axis, wherein each gyroscope of the first scissored pair has a spin motor for spinning a rotor about a rotor axis and a gimbal motor for rotating the rotor about a gimbal axis that is normal to the rotor axis and the first output axis, the first scissored pair having spin motor driver means for extracting kinetic energy from the rotors of the first scissored pair as those rotors are decelerated during a period of peak spacecraft torquing, and gimbal motor driver means for receiving extracted energy delivered from the spin motor driver means to power the gimbal motors of the first scissored pair without calling upon spacecraft bus power;

b) a second scissored pair of control moment gyroscopes for delivering an output torque to the spacecraft along a second output axis, wherein each gyroscope in the second scissored pair has a spin motor for spinning a rotor about a rotor axis and a gimbal motor for rotating the rotor about a gimbal axis that is normal to the rotor axis and to the second output axis, the second scissored pair having spin motor driver means for extracting kinetic energy from the rotors of the second scissored pair as those rotors are decelerated during said period of peak spacecraft torquing, and gimbal motor driver means for receiving extracted energy delivered from the spin motor driver means to power the gimbal motors of the second scissored pair without calling upon spacecraft bus power; and

c) a third scissored pair of control moment gyroscopes for delivering an output torque to the spacecraft along a third output axis, wherein each gyroscope in the third scissored pair has a spin motor for spinning a rotor about a rotor axis and a gimbal motor for rotating the rotor about a gimbal axis that is normal to the rotor axis and to the third output axis, the third scissored pair having spin motor driver means for extracting kinetic energy from the rotors of the third scissored pair as those rotors are decelerated during said period of peak spacecraft torquing, and gimbal motor driver means for receiving extracted energy delivered from the spin motor driver means to power the gimbal motors of the third scissored pair without calling upon spacecraft bus power.

5. An attitude control system as recited in claim 4, further comprising means for controlling gimbal angle and precession rate of the gimbal torque motors of the first, second and third scissored pairs.

6. A method of powering a control moment gyroscope on a spacecraft, the gyroscope having a rotor and a gimbal motor, the method comprising the steps of:

a) accelerating a rotor to a nominal speed during a quiescent period;

b) decelerating the rotor during a period of peak spacecraft torquing;

c) extracting stored kinetic energy from the decelerating rotor;

d) delivering the energy extracted from the decelerating rotor directly to the gimbal motor; and

e) powering the gimbal motor with the energy extracted from the decelerating rotor to impart torque to the spacecraft.

7. A method according to claim 6, further comprising the step of rotating the rotor at a desired gimbal rate to a desired gimbal angle.

8. A method according to claim 6, further comprising the step of returning the rotor to the nominal speed.

9. A method of powering a scissored pair of control moment gyroscopes on a spacecraft, each control moment gyroscope having a rotor and a gimbal torque motor, the method comprising the steps of:

a) accelerating the rotors of the scissored pair of control moment gyroscopes to a nominal speed during a quiescent period, using energy from a spacecraft power bus;

b) simultaneously decelerating the rotors of the scissored pair of control moment gyroscopes during a period of peak spacecraft torquing;

c) extracting stored kinetic energy from the decelerating rotors;

d) delivering the energy extracted from the decelerating rotors to the gimbal torque motors; and

e) powering the gimbal torque motors of the scissored pair of control moment gyroscopes with the energy extracted from the decelerating rotors to impart torque to the spacecraft, without calling upon spacecraft bus power.

10. A method according to claim 9, further comprising the step of rotating the rotors in tandem at a desired gimbal rate to desired gimbal angles.

11. A method according to claim 10, further comprising the step of returning the rotors of the scissored pair to a nominal speed.

12. A method according to claim 11, wherein the rotors of the scissored pair return to a nominal speed as the gimbal torque motors of the scissored pair precess the rotors at a desired gimbal rate.

13. A method according to claim 12, further comprising the step of controlling the rate at which the gimbal torque motors of the scissored pair precess such that the scissored pair has zero output torque.