Spin stabilization of a spacecraft for an orbit maneuver

Patent metadata

Field	Value
Publication number	US-9963248-B2
Application number	US-201615016204-A
Country	US
Kind code	B2
Filing date	Feb 4, 2016
Priority date	Feb 4, 2016
Publication date	May 8, 2018
Grant date	May 8, 2018

Abstract

Apparatus and methods for controlling a spacecraft for a transfer orbit. The spacecraft includes a momentum subsystem that stores angular momentum relative to a center of mass of the spacecraft, and a propulsion subsystem that includes electric thrusters. A controller identifies a target spin axis for the spacecraft, determines gimbal angles for electric thruster(s) that so that thrust forces from the electric thrusters are parallel to the target spin axis, and initiates a burn of the electric thruster(s) at the gimbal angles. The controller controls the momentum subsystem to compensate for a thruster torque produced by the burn of the electric thrusters. The momentum subsystem is able to produce a target angular momentum about the center of mass, where a coupling between the target angular momentum and an angular velocity of the spacecraft creates an offset torque to counteract the thruster torque.

First claim

The invention claimed is:

1. A spacecraft comprising:
a bus having a nadir side and a zenith side opposite the nadir side;
a momentum subsystem configured to produce angular momentum that couples with an angular velocity of the spacecraft;
a propulsion subsystem that includes a plurality of electric thrusters installed on the zenith side of the bus to produce a change in velocity (delta-V) on the spacecraft, wherein each of the electric thrusters is coupled to the bus by a two-axis gimbal assembly; and
a controller configured to identify a target spin axis for the spacecraft in a body-fixed frame as the spacecraft is allowed to spin during a transfer orbit, to determine gimbal angles for at least one of the electric thrusters so that thrust forces from the at least one electric thruster are parallel to the target spin axis in the body-fixed frame as the spacecraft spins during the transfer orbit, and to initiate a burn of the at least one electric thruster at the gimbal angles;
the controller is configured to control the momentum subsystem to compensate for a thruster torque in the body-fixed frame produced by the burn of the at least one electric thruster at the gimbal angles as the spacecraft spins during the transfer orbit to stabilize the spacecraft on the target spin axis within a tolerance.

2. The spacecraft of claim 1 wherein:
the momentum subsystem is configured to produce a target angular momentum, wherein a coupling between the target angular momentum and the angular velocity of the spacecraft creates an offset torque to counteract the thruster torque created from the burn of the at least one electric thruster.

3. The spacecraft of claim 2 wherein:
the controller is configured to estimate the angular velocity of the spacecraft, to estimate the thruster torque created from the burn of the at least one electric thruster, to determine the target angular momentum based on the angular velocity and the thruster torque, and to generate a command to instruct the momentum subsystem to produce the target angular momentum.

4. The spacecraft of claim 1 wherein:
the target spin axis is aligned with a target delta-V direction.

5. The spacecraft of claim 1 wherein:
the momentum subsystem comprises a reaction wheel subsystem having a plurality of reaction wheels.

6. The spacecraft of claim 1 wherein:
the momentum subsystem comprises a control momentum gyroscope (CMG).

7. The spacecraft of claim 1 further comprising:
a sensor subsystem that includes an attitude sensor configured to provide measurement data of an attitude of the spacecraft.

8. The spacecraft of claim 1 further comprising:
a sensor subsystem that includes a rate sensor configured to provide measurement data of the angular velocity of the spacecraft.

9. The spacecraft of claim 1 wherein:
the plurality of electric thrusters includes a northwest thruster, a northeast thruster, a southwest thruster, and a southeast thruster installed on the zenith side of the bus.

10. The spacecraft of claim 1 wherein:
the electric thrusters use xenon as a propellant.

11. A method for controlling a spacecraft in a transfer orbit, wherein the spacecraft comprises a bus having a nadir side and a zenith side opposite the nadir side, a momentum subsystem configured to produce angular momentum that couples with an angular velocity of the spacecraft, and a propulsion subsystem that includes a plurality of electric thrusters installed on the zenith side of the bus by a two-axis gimbal assembly, the method comprising:
identifying a target spin axis for the spacecraft in a body-fixed frame as the spacecraft is allowed to spin during the transfer orbit;
determining gimbal angles for at least one of the electric thrusters that so that thrust forces from the at least one electric thruster are parallel to the target spin axis in the body-fixed frame as the spacecraft spins during the transfer orbit;
initiating a burn of the at least one electric thruster at the gimbal angles; and
controlling the momentum subsystem to compensate for a thruster torque in the body-fixed frame produced by the burn of the at least one electric thruster at the gimbal angles as the spacecraft spins during the transfer orbit to stabilize the spacecraft on the target spin axis within a tolerance.

12. The method of claim 11 wherein controlling the momentum subsystem to compensate for a thruster torque produced by the burn of the at least one electric thruster at the gimbal angles comprises:
producing a target angular momentum with the momentum subsystem, wherein a coupling between the target angular momentum and the angular velocity of the spacecraft creates an offset torque to counteract the thruster torque created from the burn of the at least one electric thruster.

13. The method of claim 12 wherein controlling the momentum subsystem to compensate for a thruster torque produced by the burn of the at least one electric thruster at the gimbal angles comprises:
estimating the angular velocity of the spacecraft;
estimating the thruster torque created from the burn of the at least one electric thruster;
determining the target angular momentum based on the angular velocity and the thruster torque; and
generating a command to instruct the momentum subsystem to produce the target angular momentum.

14. The method of claim 11 wherein:
the target spin axis is aligned with a target delta-V direction.

15. An apparatus comprising:
a controller configured to control a spacecraft in a transfer orbit, wherein the spacecraft comprises:
a bus having a nadir side and a zenith side opposite the nadir side;
a momentum subsystem that produce angular momentum that couples with an angular velocity of the spacecraft; and
a propulsion subsystem that includes a plurality of electric thrusters installed on the zenith side of the bus, wherein each of the electric thrusters is coupled to the bus by a two-axis gimbal assembly;

the controller is configured to identify a target spin axis for the spacecraft in a body-fixed frame as the spacecraft is allowed to spin during the transfer orbit, to determine gimbal angles for at least one of the electric thrusters so that thrust forces from the at least one electric thruster are parallel to the target spin axis in the body-fixed frame as the spacecraft spins during the transfer orbit, to initiate a burn of the at least one electric thruster at the gimbal angles, and to control the momentum subsystem to compensate for a thruster torque in the body-fixed frame produced by the burn of the at least one electric thruster at the gimbal angles as the spacecraft spins during the transfer orbit to stabilize the spacecraft on the target spin axis within a tolerance.

16. The apparatus of claim 15 wherein:
the controller is configured to control the momentum subsystem to produce a target angular momentum, wherein a coupling between the target angular momentum and the angular velocity of the spacecraft creates an offset torque to counteract the thruster torque created from the burn of the at least one electric thruster.

17. The apparatus of claim 16 wherein:
the controller includes:
an estimator module configured to estimate the angular velocity of the spacecraft, and to estimate the thruster torque created from the burn of the at least one electric thruster; and
a control law module configured to determine the target angular momentum based on the angular velocity and the thruster torque, and to generate a command to instruct the momentum subsystem to produce the target angular momentum.

18

Assignees

• Boeing Co

Inventors

• Wang Qinghong W
• Sobel Alexander Jacob
• Lemke Gary
• Lui Timothy
• Lee Kangsik
• Caplin Glenn N
• Fontana Troy Allen

Classifications

• B64G1/283 Primary

  using reaction wheels · CPC title

• B64G1/36

  using sensors, e.g. sun-sensors, horizon sensors · CPC title

• B64G1/286

  using control momentum gyroscopes (CMGs) · CPC title

• B64G1/281

  Spin-stabilised spacecraft · CPC title

• B64G1/361

  using star sensors · CPC title