Flywheel controlled sun capturing and sun orientation method by using star sensor information

A star sensor, technology for capturing the sun, applied in the control field of the flywheel on the satellite, can solve the problem of not being able to capture the sun, and achieve the effect of making up for the defect that cannot be continuously oriented, and the system is simple and reliable

Active Publication Date: 2018-01-19
SHANGHAI AEROSPACE CONTROL TECH INST
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Problems solved by technology

If the sun sensor or gyro fails, it will not be possible to capture the sun and orient it to the sun
On the othe

Method used

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  • Flywheel controlled sun capturing and sun orientation method by using star sensor information
  • Flywheel controlled sun capturing and sun orientation method by using star sensor information
  • Flywheel controlled sun capturing and sun orientation method by using star sensor information

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Embodiment Construction

[0033] The present invention will be further elaborated below by describing a preferred specific embodiment in detail in conjunction with the accompanying drawings.

[0034] Such as figure 1 As shown in the coordinate system, the satellite body coordinate system b(O-X b Y b Z b ) has a vector Od, when the mission requires that the attitude of the satellite is abnormal, the vector Od always points to the sun to ensure sufficient energy supply on the satellite. Set a new coordinate system d(O-X d Y d Z d ), taking the vector Od as the X of the new coordinate system d axis, the Yd axis is perpendicular to the Z b x d plane, ie Z d Follow the right-hand rule.

[0035] Therefore, a new coordinate system d(O-X d Y d Z d ) to the satellite body coordinate system b(O-X b Y b Z b ) of the quaternion value, let it be q bd .

[0036] Satellite body coordinate system b(O-X b Y b Z b ) The quaternion relative to the inertial coordinate system i is obtained from the ...

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Abstract

Disclosed is a flywheel controlled sun capturing and sun orientation method by using star sensor information. The method comprises the following steps that 1, measured information qbi of a start sensor and direction qsi of sun in an inertial system are used to calculate sun vector coordinate system quaternion qsd conveted from a vector coordinate system d in a satellite star body; 2, characteristics of the sun vector coordinate system quaternion qsd conveted from the vector coordinate system d, maximum angular velocity Omega max of the attitude maneuver and flywheel output torque Mm are used to calculate parameter Phi, and an attitude maneuver path is planned according to the parameter Phi; and 3, a control law is designed according to the attitude maneuver path planned in the step 2, andthe control quantity is allocated to a flywheel group to control a satellite to realize sun orientation of a vector d. The flywheel controlled sun capturing and sun orientation method is a supplementorientation mean of sun orientation by using a sun sensor, a system is simple and reliable, the sun orientation function in a shadow area can be implemented, and the defect that the sun sensor cannotbe continuously oriented is remedied.

Description

technical field [0001] The invention relates to the technical field of control of flywheels on satellites, in particular to a flywheel control method for capturing the sun and orienting to the sun using star sensor information. Background technique [0002] The angular velocity of the satellite can be controlled within a certain range after the abnormal attitude of the satellite is damped by the rate, and this angular velocity is within the dynamic range of the normal work of the star sensor. Using the attitude quaternion of the satellite measured by the star sensor relative to the inertial coordinate system, and the orientation information of the sun in the inertial coordinate system calculated according to the ephemeris on the star, the sun can be calculated relative to a certain vector on the star (the vector points to the sun) quaternion with guaranteed energy). According to this quaternion, the space axis n around which a certain vector on the star points to the sun an...

Claims

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Application Information

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IPC IPC(8): B64G1/28
Inventor 李英波蒋光伟张子龙聂章海谭晓宇
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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