Device and method for determining the attitude of a satellite equipped with gyroscopic actuators, and satellite carrying such a device

Patent metadata

Field	Value
Publication number	US-11498704-B2
Application number	US-202017598201-A
Country	US
Kind code	B2
Filing date	Mar 17, 2020
Priority date	Mar 25, 2019
Publication date	Nov 15, 2022
Grant date	Nov 15, 2022

Abstract

A device for determining an attitude of a satellite is disclosed, the satellite having an attitude control system comprising a gyroscopic actuator including a flywheel mounted so as to be rotatable around an axis of rotation and carried by a gimbal articulated to rotate around an axis of rotation. The device includes an attitude sensor configured to measure the attitude of the satellite, a position sensor configured to measure the angular position of the gimbal around its axis of rotation, a speed sensor configured to measure the rotational speed of the flywheel, and a processing circuit configured to determine the attitude of the satellite by using the measurement of the angular position of the gimbal, the measurement of the rotational speed of the flywheel, and the measurement of the attitude of the satellite.

First claim

The invention claimed is:

1. A device for determining an attitude of a satellite, said satellite being provided with an attitude control system comprising at least one gyroscopic actuator, said at least one gyroscopic actuator comprising a flywheel mounted so as to be rotatable around an axis of rotation, said flywheel being carried by a gimbal articulated to rotate around an axis of rotation, said device comprising an attitude sensor capable of measuring the attitude of said satellite, wherein said device comprises:
a position sensor configured to measure the angular position of the gimbal around its axis of rotation,
a speed sensor configured to measure the rotational speed of the flywheel,
calculation means configured to determine the attitude of the satellite by using the measurement of the angular position of the gimbal carried out by the position sensor, the measurement of the rotational speed of the flywheel carried out by the speed sensor, and the measurement of the attitude of the satellite carried out by the attitude sensor.

2. The device according to claim 1 , wherein the attitude sensor comprises one or more star trackers.

3. The device according to claim 1 , wherein the calculation means comprises a rate gyro emulation module configured to determine a quantity, called the angular increment, representative of the variation in attitude of the satellite induced by the at least one gyroscopic actuator, by using the measurement of the angular position of the gimbal carried out by the position sensor and the measurement of the rotational speed of the flywheel carried out by the speed sensor, the attitude of the satellite being determined by using the angular increment and the measurement of the attitude of the satellite carried out by the attitude sensor.

4. The device according to claim 3 , wherein the calculation means comprises an estimation filter which receives the angular increment and the measurement of the attitude of the satellite as input, and which outputs an estimate of the attitude of the satellite.

5. The device according to claim 1 , wherein, the satellite being an observation satellite alternating between different attitude control phases comprising maneuvering phases and image capture phases, the calculation means is configured to apply weighting coefficients in order to weight the respective contributions, during the attitude determination, of the measurement from the attitude sensor on the one hand and of the measurements from the position sensor and speed sensor on the other hand, the weighting coefficients being dependent on the attitude control phase in progress and being determined in order to:
during maneuvering phases: increase the contribution of the measurement from the attitude sensor relative to the contribution of the measurements from the position sensor and speed sensor,
during image capture phases: increase the contribution of the measurements from the position sensor and speed sensor relative to the contribution of the measurements from the attitude sensor.

6. The device according to claim 1 , wherein, the gimbal of the at least one gyroscopic actuator being articulated to rotate around two different axes and the position sensor being able to measure the respective angular positions of the gimbal around said two axes of rotation, the calculation means is configured to determine the attitude of the satellite by using the measurements of the respective angular positions of said gimbal around said two axes of rotation, carried out by the position sensor.

7. The device according to claim 1 , wherein, the attitude control system comprising several gyroscopic actuators each comprising a gimbal, a flywheel, a position sensor, and a speed sensor, the calculation means is configured to determine the attitude of the satellite by using the measurements of the angular positions of the gimbals carried out by the position sensors, the measurements of the rotational speeds of the flywheels carried out by the speed sensors, and the measurement of the attitude of the satellite carried out by the attitude sensor.

8. A satellite comprising an attitude control system comprising at least one gyroscopic actuator, said at least one gyroscopic actuator comprising a flywheel mounted so as to be rotatable around an axis of rotation, said flywheel being carried by a gimbal articulated to rotate around an axis of rotation, wherein the satellite comprises a device for determining attitude according to claim 1 .

9. The satellite according to claim 8 , wherein it is without any rate gyros.

10. A method for determining an attitude of a satellite, said satellite being provided with an attitude control system comprising at least one gyroscopic actuator, said at least one gyroscopic actuator comprising a flywheel mounted so as to be rotatable around an axis of rotation, said flywheel being carried by a gimbal articulated to rotate around an axis of rotation, the satellite further comprising an attitude sensor configured to measure the attitude of said satellite,
wherein the at least one gyroscopic actuator being previously provided with a position sensor configured to measure the angular position of the gimbal around its axis of rotation, and with a speed sensor configured to measure the rotational speed of the flywheel around its axis of rotation, the method comprises steps of:
measuring the angular position of the gimbal around its axis of rotation, by means of said position sensor,
measuring the rotational speed of the flywheel around its axis of rotation, by means of said speed sensor,
measuring the attitude of the satellite, by means of said attitude sensor,
determining the attitude of the satellite, by means of a processing circuit, by using the measurement of the angular position of the gimbal carried out by the position sensor, the measurement of the rotational speed of the flywheel carried out by the speed sensor, and the measurement of the attitude of the satellite carried out by the attitude sensor.

11. The method according to claim 10 , comprising a step of determining a quantity, called the angular increment, representative of the variation in attitude of the satellite induced by the at least one gyroscopic actuator, by using the measurement of the angular position of the gimbal carried out by the position sensor and the measurement of the rotational speed of the flywheel carried out by the speed sensor, the attitude of the satellite being determined by using the angular increment and the measurement of the attitude of the satellite carried out by the attitude sensor.

12. The method according to claim 10 , wherein, the satellite being an observation satellite alternating between different attitude control phases comprising maneuvering phases and image capture phases, said method comprises a use of weighting coefficients to weight the respective contributions, during the attitude determination, of the measurement from the attitude sensor on the one hand and of the measurements from the position sensor and speed sensor on the other hand, the weighting coefficients being dependent on the attitude control phase in progress and being determined in order to:
during maneuvering phases: increase the contribution of the measurement from the attitude sensor relative to the contribution of the measurements from the position sensor and speed sensor,
during image capture phases: increase the contribution of the measurements from the position sensor and speed sensor relative to the contribution of the measurements from the attitude sensor.

13. The method according to claim 10 , wherein the gimbal of the at least one gyroscopic actuator being articulated to

Assignees

• Airbus Defence & Space Sas

Inventors

• Laurens Philippe
• Lesprier Jeremy

Classifications

• B64G1/286

  using control momentum gyroscopes (CMGs) · CPC title

• B64G1/244

  Spacecraft control systems · CPC title

• B64G1/361

  using star sensors · CPC title

• B64G1/1021 Primary

  Earth observation satellites · CPC title

• G01C21/24

  specially adapted for cosmonautical navigation · CPC title