A Satellite Spinning Sun Acquisition Method Based on Calculation of Sun Vector by Gyro Integral
A solar vector and satellite technology, which is applied in the field of satellite spin solar capture, can solve the problems of entering a safe mode and insufficient reliability, and achieves the effect of fast capture speed and favorable thermal design.
Active Publication Date: 2019-10-01
SHANGHAI ENG CENT FOR MICROSATELLITES
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[0005] Aiming at the insufficient reliability of satellites in the prior art during orbit-to-sun acquisition operation, and avoiding the temporary failure of orbit data to enter the safe mode, according to an embodiment of the present invention, a method for calculating the sun vector based on gyroscope integration is provided. The satellite spin sun acquisition method includes: obtaining the sun vector of the satellite body coordinate system; calculating and obtaining the satellite attitude quaternion; performing singular point processing and calculating the three-axis control torque; limiting the three-axis control torque; and control torque distribution and Control torque vector limiter
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[0035] In the following description, the present invention is described with reference to various examples. One skilled in the art will recognize, however, that the various embodiments may be practiced without one or more of the specific details, or with other alternative and / or additional methods, materials, or components. In other instances, well-known structures, materials, or operations are not shown or described in detail so as not to obscure aspects of the various embodiments of the invention. Similarly, for purposes of explanation, specific quantities, materials and configurations are set forth in order to provide a thorough understanding of embodiments of the invention. However, the invention may be practiced without these specific details. Furthermore, it should be understood that the various embodiments shown in the drawings are illustrative representations and are not necessarily drawn to scale.
[0036] In this specification, reference to "one embodiment" or "the...
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The invention discloses a satellite spin sun capture method based on gyro integral for solar vector calculation. The satellite spin sun capture method based on the gyro integral for the solar vector calculation comprises the steps that a satellite body coordinate system solar vector is obtained; a satellite attitude quaternion is calculated and obtained; a singular point is processed and triaxialcontrol torque is calculated; the triaxial control torque is subjected to amplitude limiting; and the torque distribution is controlled and amplitude limiting of the torque vector is controlled.
Description
technical field [0001] The invention relates to the field of satellite attitude control, in particular to a satellite spin sun acquisition method based on gyroscope integral calculation of sun vector. Background technique [0002] During the satellite’s in-orbit sun capture operation, magnetometers, sun sensors, star sensors, gyroscopes, etc. are generally used as sensors for satellite attitude measurement, and magnetic torque devices, reaction wheels or thrusters are used as actuators for sun capture. . [0003] The short-term control torque generated by the magnetic torquer is small, so it usually takes a long time to use the magnetic torquer as the actuator to capture the sun; the sun capture speed is fast when the thruster is used, but it is usually necessary to turn on the propulsion heater in advance to perform Preheating requires more energy consumption and propellant consumption. When wheel control is used to measure the sun, the three-axis attitude determination i...
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IPC IPC(8): G05D1/08B64G1/28
Inventor 戴正升刘国华王政伟卞晶刘琦姚小松
Owner SHANGHAI ENG CENT FOR MICROSATELLITES