Method and device for controlling satellite attitude and steering using a gyrodyne cluster

• US 7,171,290 B2
• Filed: 06/24/2002
• Issued: 01/30/2007
• Est. Priority Date: 06/26/2001
• Status: Expired due to Term

• Current Assignee: EADS Astrium SAS (Airbus SE), Splashpower Limited
• Original Assignee: EADS Astrium SAS (Airbus SE)
• Inventors: Defendini, Ange, Lagadec, Kristen, Morand, Julien
• Primary Examiner(s): Zanelli; Michael J.
• Application Number:
  US10/482,031
• Publication Number:
  US 20040167683A1
• Time in Patent Office: 1,681 Days
• Field of Search: None
• US Class Current: 701/13
• CPC Class Codes: B64G 1/244 Spacecraft control systems

Abstract

In order to control the attitude of a satellite having at least four gyroscopic actuators with respective spinners mounted on gimbals steerable about axes parallel to one or the other of only two different directions that are fixed relative to the satellite, the attitude of the satellite is measured using sensors on board the satellite, the control torque required to perform an attitude-changing maneuver is calculated, local linearization calculation is performed based on pseudo-inversion of the Jacobean matrix of the function associating the orientations of the actuator gimbals with the total angular momentum of the cluster in order to determine a new gimbal orientation, and precession speeds of at least one of the gimbals of the actuators are controlled to deliver the control torque for reaching the desired configuration.

Claims

1. A method of controlling the attitude of a satellite having a cluster of at least four gyroscopic actuators with respective spinners mounted on gimbals steerable about axes parallel to one or the other of only two different directions that are fixed relative to the satellite so as to form at least two groups of actuators of which one group has at least two actuators, the method comprising the steps of:

measuring the attitude of said satellite by means of sensors on board said satellite;

calculating a control torque required to perform an attitude-changing maneuver;

calculating local linearization based on pseudo-inversion of the Jacobean matrix of the function associating the orientations of said actuator gimbals with the total angular momentum of said cluster in order to determine new orientations for said gimbals; and

commanding precession speeds of at least one of said actuator gimbals so as to deliver said control torque for achieving the desired configuration;

wherein the step of determining said new orientations is performed by applying a constraint of seeking a cluster configuration remote from singular configurations by sharing between said two groups of actuators that component of said total angular momentum of said cluster which is perpendicular to both of said two directions.

2. The method according to claim 1, comprising a step of adopting, as a criterion for remoteness between a configuration of the angles of said gimbals in said cluster and a singular configuration, the product of two simpler criteria that apply separately to each of said two groups of actuators.

3. The method according to claim 2, wherein for a group constituted by two actuators each carrying a non-dimensional angular momentum of unity norm, said criterion for remoteness between a configuration of gimbal angles and a singular configuration is selected as:

being zero when the angle between the two angular momentum vectors carried by said two actuators is zero or flat; and

reaching a maximum when the angle between the two angular momentum vectors carried by said two actuators is close to 90°

.

4. The method according to claim 3, wherein said criterion for remoteness between a configuration of gimbal angles and a singular configuration is determined by using one of the following parameters:

the norm of the vector product of two angular momentum vectors carried by said two actuators;

the absolute value of the sine of the angle formed between the two angular momentum vectors carried by said two actuators;

the area of a triangle having two sides constituted by the angular momentum vectors carried by said two actuators, their origins coinciding; and

the difference between unity and the absolute value of the scalar product of the two angular momentum vectors carried by said two actuators.

5. The method according to claim 2, wherein, for a group of actuators being constituted by three actuators each carrying a non-dimensional angular momentum of unity norm, said criterion for remoteness between a configuration of gimbal angles and a singular configuration is defined in such a manner as to cancel when one of the angles formed between any two of the three angular momentum vectors carried by said three actuators is zero and so as to reach its maximum when said angles are close to 120°

.

6. The method according to claim 5, wherein said criterion for remoteness between a configuration of gimbal angles and a singular configuration is determined by using one of the following parameters:

the sum of the three vector products between pairs of the angular momentum vectors carried by said three actuators; and

the area of a triangle whose vertices coincide with the vertices of the angular momentum vectors carried by said three actuators, their origins coinciding.

7. The method according to claim 1 for controlling said satellite in application of a relationship that is determined over time, wherein a final configuration remote from singular configurations is sought continuously by permanently deflecting the cluster configuration so as to occupy the local maximum of a criterion for remoteness between a configuration of gimbal angles and a singular configuration.

8. The method according to claim 1, wherein a final configuration remote from singular configurations is sought when it is detected that the remoteness between the current configuration and an associated singular configuration has dropped below a predetermined threshold.

9. The method according to claim 1, wherein, in order to perform a determined attitude maneuver reaching a final configuration that is remote from singular configurations, attitude is controlled by associating open loop control with closed loop control.

10. The method according to claim 9, wherein prior calculation is used to establish a correspondence table between various cluster angular momentums needed for various satellite maneuvers and respective associated optimum cluster configurations so as to reach a final configuration that is remote from singular configurations.

11. The method according to claim 9, wherein the search for a final configuration remote from singular configurations provides directly and in analytic manner an optimum cluster configuration delivering the requested cluster angular momentum needed for maneuvering said satellite.

12. The method according to claim 7, which is implemented in advance on the basis of prior knowledge of a maneuver that is to be performed, and wherein the satellite attitude maneuver is performed by using a resulting trajectory in an open loop in attitude control associating an open loop control with a closed loop control for bringing said satellite into the desired final attitude.