Three-axis sun-oriented control method of satellite for guaranteeing satellite-earth link

A technology of directional control and satellite-ground link, applied in vehicle position/route/altitude control, attitude control, non-electric variable control and other directions, which can solve the problems of small maneuvering angle and inability to guarantee rough ground pointing requirements.

Active Publication Date: 2016-11-23
SHANGHAI AEROSPACE CONTROL TECH INST
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Problems solved by technology

This mode is based on the sun sensor for two-axis orientation to the sun, that is, the star is slowly rotating or inertial to the sun axis, and the measurement and control antenna that is originally in the direction of the ground may be facing the sky, which cannot guarantee the coarse ground pointing r

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  • Three-axis sun-oriented control method of satellite for guaranteeing satellite-earth link
  • Three-axis sun-oriented control method of satellite for guaranteeing satellite-earth link
  • Three-axis sun-oriented control method of satellite for guaranteeing satellite-earth link

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Embodiment Construction

[0044] Hereinafter, in conjunction with the accompanying drawings, a preferred embodiment is described in detail to further illustrate the present invention.

[0045] Under the condition of “allowing the use of star-sensitivity to the sun”, use the sun sensor to realize the flywheel coarse alignment in the future, and use the solar azimuth for closed-loop control for rolling and yaw. The pitch axis uses gyro integral to control the star at 0.01 degree / sec. Angular velocity movement. When the star sensitive output is valid, judge the attitude quaternion Q of the star relative to the satellite orbit coordinate system ob The attitude quaternion Q of the satellite orbital coordinate system relative to the reference coordinate system for the orientation to the sun or The error between the quaternion Q rb , According to the error quaternion Q rb The sign of, controls the star to rotate in the opposite polarity to Qis (the quaternion of the reference coordinate system for the solar orie...

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Abstract

The invention discloses a three-axis sun-oriented control method of a satellite for a guaranteeing satellite-earth link. The three-axis sun-oriented control method comprises the following steps: solving a projection of a sun vector under a satellite orbit coordinate system according to the sun vector calculated according to a satellite orbit; establishing a sun-oriented reference coordinate system according to the satellite orbit and the definition of the satellite polarity, and calculating an attitude quaternion of the sun-oriented reference coordinate system relative to the satellite orbit coordinate system; calculating an error quaternion between an attitude quaternion of a star relative to the satellite orbit coordinate system and the attitude quaternion of the sun-oriented reference coordinate system relative to the satellite orbit coordinate system; carrying out attitude reference tracking according to a symbol of the error quaternion; and when continuously meeting that the error quaternion is smaller than a preset threshold value, establishing a star sensor sun-oriented sign, carrying out three-axis stabilization sun-oriented control by virtue of a star sensor, and otherwise, continuing to carry out two-axis sun-oriented control based on sun sensor. By virtue of the three-axis sun-oriented control method, the smoothness of the satellite-earth link after the sun orientation of a sailboard can be guaranteed, and a near-optimal maneuvering path is guaranteed when a sun-oriented maneuvering manner is changed into a ground-oriented maneuvering manner.

Description

Technical field [0001] The invention relates to a satellite orientation control method, in particular to a satellite three-axis orientation control method to the sun that guarantees a satellite-to-earth link. Background technique [0002] Sun-synchronous orbit satellites often regard the solar panel facing the sun as one of the conventional control modes or as a safety control mode, because this mode can ensure that the solar panel is illuminated, that is, to ensure sufficient energy supply. This mode is based on the two-axis orientation of the sun sensor to the sun, that is, the star is slowly rotating or inertial to the sun axis, and the measurement and control antenna that is originally in the direction of the earth may be up to the sky, which cannot guarantee the demand for coarse earth orientation; During the satellite orientation to Japan, in order to ensure that it can quickly turn to the ground attitude after receiving the mission, it is hoped that the attitude maneuver a...

Claims

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Application Information

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IPC IPC(8): G05D1/08
CPCG05D1/0825
Inventor 杜宁尹海宁赖京袁彦红孙锦花沈煜昊
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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