Zero momentum magnetic control sun capture device and method of satellite

Abstract

The invention discloses a zero momentum magnetic control sun capture device and method of a satellite. The device comprises a 0-1 type sun sensor, a magnetometer and a magnetic torquer, wherein the 0-1 type sun sensor and the magnetometer are matched, and are used for performing satellite attitude measurement; the output of the magnetic torquer acts on the satellite body after delay, and is used for providing control moment for the satellite in the satellite rate damping process and controlling the attitude angle deviation to be less than a preset threshold value, so as to realize zero momentum magnetic control sun capture; when the 0-1 type sun sensor judges that the sun appears in the field of view, the double-vector attitude determination FORM algorithm is adopted, and a three-axis attitude matrix of the satellite is determined through the 0-1 type sun sensor and the magnetometer; when the 0-1 type sun sensor judges that the satellite enters the shadow zone, the satellite elevation angle is determined through the magnetometer. According to the zero momentum magnetic control sun capture device and method, the single machine configuration of the control system is simplified, the reliability of an attitude control subsystem is improved, and the resources on the satellite are saved.

Description

technical field [0001] The invention relates to the technical field of aerospace measurement and control, in particular to a zero-momentum magnetically controlled sun capture device and method suitable for microsatellites. Background technique [0002] At present, in order to achieve the purpose of rapid derotation during the orbiting stage and safety mode, the satellites mostly use thrusters or magnetic torque control methods to achieve three-axis large angular velocity rate damping. When the three-axis angular velocity of the satellite decreases to the preset threshold, the star sensor is introduced as the attitude sensor, and the reaction flywheel group is used as the actuator, and the three-axis wheel control is used to make the normal line of the satellite sail point to the sun, so as to realize the sun capture and ensure the safety of the satellite. energy supply. [0003] The disadvantage of the existing technology is: using thrusters in the rate damping stage, altho...

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Problems solved by technology

[0003] The disadvantage of the existing technology is: using thrusters in the rate damping stage, although the purpose of fast derotation can be achieved, but the thrusters used on satellites are expensive and not mature, which not only increases the complexity of the control system , and there are risks; in the sun capture stage, the introduction of star sensors, gyroscopes, flywheels and other complex and high-power stand-alone machines will not only consume a lot of resources on the star, but the rapid saturation of the flywheel may even cause the attitude of the entire star to lose control

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