Method for achieving satellite three-axis stable control through single control moment gyroscope and two flywheels

Abstract

The invention relates to a method for achieving satellite three-axis stable control through a single control moment gyroscope and two flywheels. A ground measurement and control station remotely controls a satellite to control the attitude through a thruster. Angular momentum corresponding to the rotating speed of the CMG inner rotor is obtained according to the rotating speed instruction of the CMG inner rotor; a magnetic unloading target angular momentum is set according to the CMG outer frame position and the effective rotating speed instructions of the two flywheels; a changed angular momentum control instruction is calculated according to the instruction torque, the CMG frame angular position, the frame rotating speed, the system control period, the effective angular momentum controlinstructions of the two flywheels and the like, and the CMG frame angle is resolved: allowing single CMG control, selecting single CMG access, effectively connecting the two flywheels, and controllingthe satellite attitude by using the flywheels. For satellites adopting flywheels and control moment gyroscopes as attitude control main actuating mechanisms, stable attitude control can be realized 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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