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METHOD OF COMMANDING AN ATTITUDE CONTROL SYSTEM AND ATTITUDE CONTROL SYSTEM OF A SPACE VEHICLE

2013
Online Patent
Zugriff:
View record in USPTO Patent Applications (Volltext)

A method for controlling an attitude control system (30) for a space vehicle (10), the attitude of the space vehicle being controlled during at least one preparation phase followed by an observation phase during which an image capture is performed. In an attitude control system that includes a maneuvering subsystem (300) which includes at least one reaction wheel, the method includes, during the at least one preparation phase, a preparation step (50), during which commands are issued to the maneuvering subsystem in order to control the attitude of the space vehicle, followed by a step (55) of stopping the at least one reaction wheel prior to the observation phase. In addition, during the observation phase, a fine control subsystem (310) having a lower vibration signature than that of the maneuvering subsystem, is sent commands in order to control the space vehicle's attitude. An attitude control system for a space vehicle is also described.

Titel:
METHOD OF COMMANDING AN ATTITUDE CONTROL SYSTEM AND ATTITUDE CONTROL SYSTEM OF A SPACE VEHICLE
Link:
Veröffentlichung: 2013
Medientyp: Patent
Sonstiges:
  • Nachgewiesen in: USPTO Patent Applications
  • Sprachen: English
  • Document Number: 20130105633
  • Publication Date: May 2, 2013
  • Appl. No: 13/637668
  • Application Filed: March 28, 2011
  • Assignees: CENTRE NATIONAL D'ETUDES SPATIALES CNES (Paris, FR), ASTRIUM SAS (Paris, FR)
  • Claim: 1- Method for controlling an attitude control system (30) of a space vehicle (10), the attitude control system (30) comprising a maneuvering subsystem (300) which comprises at least one reaction wheel, and the attitude of the space vehicle (10) being controlled during at least one preparation phase followed by an observation phase during which an image capture is performed; characterized in that said method comprises, during the at least one preparation phase: a preparation step (50), during which commands are issued to the maneuvering subsystem (300) in order to control the attitude of the space vehicle (10), followed by a step (55) in which the at least one reaction wheel is stopped, during which the speed of rotation of the at least one reaction wheel is set to a substantially zero value prior to said observation phase, and in that, during the observation phase, commands are issued to a fine control subsystem (310) having a lower vibration signature than that of the maneuvering subsystem (300), in order to control the attitude of the space vehicle (10).
  • Claim: 2- Method according to claim 1, characterized in that the step (55) in which the at least one reaction wheel is stopped comprises a sub-step (550) of closed-loop deceleration of said at least one reaction wheel.
  • Claim: 3- Method according to claim 1, characterized in that the step (55) in which the at least one reaction wheel is stopped comprises a sub-step (551) of open-loop braking the at least one reaction wheel.
  • Claim: 4- Method according to claim 3, characterized in that, in a maneuvering subsystem (300) whose at least one reaction wheel is driven in rotation by a polyphase electric motor, the open-loop braking sub-step (551) consists in short-circuiting the phases of said polyphase electric motor.
  • Claim: 5- Method according to claim 3, characterized in that the open-loop braking sub-step (551) is executed when the speed of rotation of the at least one wheel is lower than a predefined threshold.
  • Claim: 6- Method according to claim 1, characterized in that the preparation step (50) comprises a maneuvering sub-step (501) during which commands are issued to the maneuvering subsystem (300) to tilt the space vehicle's attitude from one observation attitude to another and a sub-step (502) during which commands are sent to the maneuvering subsystem (300) to stabilize the space vehicle's (10) attitude around the targeted observation attitude.
  • Claim: 7- Method according to claim 1, characterized in that the preparation step (50) comprises a sub-step (503) of offloading the maneuvering subsystem (300), during which all or part of the angular momenta caused by external disturbance torques are compensated for.
  • Claim: 8- Method according to claim 7, characterized in that the offloading is executed by sending commands to the fine control subsystem (310) and/or by sending commands to an offloading subsystem (320) of the attitude control system (30).
  • Claim: 9- Method according to claim 1, characterized in that, in a maneuvering subsystem (300) that comprises a plurality of reaction wheels configured such that there exists at least one vector of rotation speeds, not all equal to zero, called “maneuvering subsystem kernel (300)”, for which the sum of the elementary angular momenta generated by each of said reaction wheels is substantially zero, the preparation step (50) comprises, at the start of the at least one preparation phase, a sub-step (500) of accelerating the reaction wheels around the maneuvering subsystem kernel (300).
  • Claim: 10- Method according to claim 9, characterized in that the preparation step (50) comprises a sub-step (504) of decelerating the reaction wheels around the maneuvering subsystem kernel (300), prior to the step (55) of stopping the reaction wheels.
  • Claim: 11- Method according to claim 1, characterized in that it comprises, during the observation phase, a step (60) of maintaining the at least one reaction wheel stopped, during which the speed of rotation of each reaction wheel is kept at a substantially zero value.
  • Claim: 12- Attitude control system (30) for a space vehicle (10), comprising a maneuvering subsystem (300) comprising at least one reaction wheel, used to control the space vehicle's (10) attitude during at least one preparation phase, which at least one preparation phase is followed by an observation phase during which an image capture is to be performed, characterized in that said system comprises means adapted to stop the at least one reaction wheel before said observation phase, and in that it comprises a fine control subsystem (310) having a lower vibration signature than that of the maneuvering subsystem (300), used to control the space vehicle's (10) attitude during the observation phase.
  • Claim: 13- System (30) according to claim 12, characterized in that it comprises an offloading subsystem (320) adapted to compensate for all or part of the angular momenta caused by external disturbance torques.
  • Claim: 14- Method according to claim 1, characterized in that the step (55) in which the at least one reaction wheel is stopped comprises a sub-step (551) of open-loop braking the at least one reaction wheel.
  • Claim: 15- Method according to claim 3, characterized in that the open-loop braking sub-step (551) is executed when the speed of rotation of the at least one wheel is lower than a predefined threshold.
  • Current U.S. Class: 244/165
  • Current International Class: 64

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