Attitude control device for a satellite and method for controlling the attitude of a satellite

Patent metadata

Field	Value
Publication number	US-11535404-B2
Application number	US-201916506071-A
Country	US
Kind code	B2
Filing date	Jul 9, 2019
Priority date	Jul 9, 2018
Publication date	Dec 27, 2022
Grant date	Dec 27, 2022

Abstract

An attitude control apparatus for a satellite includes: at least three electric motors, wherein the at least three electric motors are arranged in such a way that a torque may be generated with any orientation of an associated torque vector, and a controller, wherein the controller is configured to drive the at least three electric motors based on a torque controller. The torque controller is adapted to operate the at least three electric motors outside a rest state only when an acceleration torque and a braking torque are required to execute an agile attitude change maneuver. There is also described an associated method.

First claim

The invention claimed is:

1. An attitude control apparatus for a satellite, the attitude control apparatus comprising:
at least three electric motors arranged to enable a torque to be generated with any orientation of an associated torque vector, and said at least three electric motors being configured to generate at least a torque of 0.09 newton-meters per kilogram of net mass;
a controller configured to drive said at least three electric motors based on a torque control; and
wherein the torque control of said controller is configured to
operate said at least three electric motors in a rest state where rotors of said at least three electric motors do not rotate; and
operate said at least three electric motors outside the rest state only when an acceleration torque and a braking torque are required in order to execute an agile attitude change maneuver, wherein the agile attitude change maneuver has a rotation rate of greater than 1 degree per second.

2. The attitude control apparatus according to claim 1 , wherein each of said at least three electric motors has a flywheel mechanically coupled to a rotor of the respective said electric motor.

3. The attitude control apparatus according to claim 1 , wherein said at least three electric motors are configured to generate at least a torque of 0.45 newton-meters per kilogram of net mass.

4. The attitude control apparatus according to claim 1 , wherein said at least three electric motors include at least one fourth electric motor, wherein said at least four electric motors are arranged in a tetrahedral arrangement such that, even if one of said electric motors fails, a torque at any orientation of an associated torque vector may be generated with the respectively remaining three electric motors.

5. The attitude control apparatus according to claim 1 , further comprising at least one tethered gyroscope, and wherein said controller is further configured to additionally drive said at least one tethered gyroscope.

6. The attitude control apparatus according to claim 1 , wherein said controller is further configured to drive said at least three electric motors so as to execute a normal attitude change maneuver of the satellite.

7. The attitude control apparatus according to claim 1 , configured to at least partially recover energy that has been converted in order to apply the torque.

8. The attitude control apparatus according to claim 1 , wherein said at least three electric motors have an interlock, said interlock being configured to enable said at least three electric motors to independently and irreversibly release the interlock by applying a corresponding torque.

9. The attitude control apparatus according to claim 1 , wherein said controller is configured to control the torque based on a torque characteristic curve.

10. An attitude control method for a satellite, the satellite having an attitude control apparatus with at least three electric motors and a controller, wherein the at least three electric motors are arranged in such a way that a torque may be generated with any orientation of an associated torque vector, and the at least three electric motors being configured to generate at least a torque of 0.09 newton-meters per kilogram of net mass, wherein the controller is configured to drive the at least three electric motors based on a torque controller, and wherein the torque controller is configured to operate said at least three electric motors in a rest state where rotors of said at least three electric motors do not rotate and to operate the at least three electric motors outside the rest state only when an acceleration torque and a braking torque are required in order to execute an agile attitude change maneuver, wherein the agile attitude change maneuver has a rotation rate of greater than 1 degree per second, the method comprising the following steps:
receiving a target orientation of the satellite;
calculating with the controller an acceleration torque and a braking torque based on a comparison between the target orientation and an actual orientation of the satellite; and
generating the calculated acceleration torque and the calculated braking torque by driving the at least three electric motors with the controller.

Assignees

• Deutsch Zentr Luft & Raumfahrt

Inventors

• Halle Winfried
• Terzibaschian Thomas
• Raschke Christian
• Baerwald Wolfgang
• Amiques Xavier
• Kotz Andreas

Classifications

• B64G1/36

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

• B64G1/244 Primary

  Spacecraft control systems · CPC title

• G06T7/70

  Determining position or orientation of objects or cameras (camera calibration G06T7/80) · CPC title

• B64G1/283 Primary

  using reaction wheels · CPC title

• B64G1/285

  using momentum wheels · CPC title