A Method of Realizing Three-Axis Stable Control of Satellite Using Single Control Moment Gyro and Two Flywheels

Abstract

The invention relates to a method for realizing satellite three-axis stable control with a single control moment gyroscope and two flywheels. The ground measurement and control station remotely controls the satellite using a thruster to control the attitude; according to the CMG inner rotor speed instruction, the angular momentum corresponding to the CMG inner rotor speed is obtained ;According to the position of the CMG outer frame and the effective rotational speed commands of the two flywheels, set the target angular momentum of magnetic unloading; , calculate the changed angular momentum control command, solve the CMG frame angle: allow single CMG control, select single CMG access, effective two flywheel access, use flywheel to control satellite attitude. For a satellite using a flywheel and a control moment gyroscope as the main actuators for attitude control, the invention can realize attitude stability control under the condition that only one control moment gyroscope and two reaction flywheels are effective on the satellite.

Description

technical field [0001] The invention belongs to satellite attitude control technology, relates to the satellite attitude control technology of "flywheel + control torque gyroscope" combined executive mechanism, in particular to a method for realizing satellite three-axis stable control through a single control moment gyroscope and two flywheels. Background technique [0002] Manipulation laws represent the distribution or solution of control torque commands. Since the torque output of the reaction flywheel is generated by the change of angular momentum, its manipulation method is relatively simple. For the control moment gyroscope, its steering law needs to be designed according to different requirements. [0003] Because the control moment gyro is realized by changing the output direction of angular momentum, when only one control moment gyro is working normally on the star, the control moment gyro will generate torque in the Z direction while outputting the torque in the ...

AI Technical Summary

Problems solved by technology

[0003] Since the control moment gyro is realized by changing the output direction of angular momentum, when only one control moment gyro is working normally on the star, when the control moment gyro outputs the torque in the X direction, it will also generate torque in the Z direction, and the two directions The torque ratio generated is related to the current angular position of the frame, so the required command torque cannot be accurately output

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