Spacecraft high-accuracy speediness attitude maneuver method based on single gimbal control moment gyro (SGCMG) and reaction wheel (RW)

Abstract

The invention discloses a spacecraft high-accuracy speediness attitude maneuver method based on a single gimbal control moment gyro (SGCMG) and a reaction wheel (RW) and relates to a spacecraft high-accuracy speediness attitude maneuver method which is used for achieving spacecraft high-accuracy speediness attitude maneuver. According to the method, a control moment gyro (CMG) and the RW are used as a combination executing mechanism to achieve the spacecraft high-accuracy speediness attitude maneuver. Angular speed of winding around an Euler main shaft is divided into three sections. Needed controlling torque is generated through the CMG in an accelerating section and a braking section. After a constant speed section and the braking section are finished, a compensate torque generated by the RW is adopted to guarantee that the angular speed is kept near a steady state value so that the spacecraft high-accuracy speediness attitude maneuver is achieved. The method is suitable for the attitude maneuver condition that a spacecraft is provided with the CMG and the RW so that rapid maneuver of the spacecraft is achieved and attitude directing in high accuracy and stability are guaranteed. The method is suitable for maneuver control of the spacecraft.

Description

technical field [0001] The invention relates to a high-precision and fast attitude maneuvering method for a spacecraft. Background technique [0002] The actuator of the spacecraft control system through the exchange of angular momentum usually has a flywheel and a control moment gyro (CMG). and dual frame control moment gyro (DGCMG). [0003] The speed of RW is zero when it is not working, and it generates control torque by accelerating or decelerating. The characteristic is that the generated torque is small, but the control precision is high, and it is usually applied to high-precision three-axis stabilized satellites. [0004] SGCMG has only one frame, and the rotation speed of the rotor is constant. It generates gyro torque through the rotation of the frame, and then acts on the spacecraft body. The characteristic is that the generated control torque is large, but the control accuracy is relatively low, and it is generally used in the attitude control of large spacec...

AI Technical Summary

Problems solved by technology

The characteristic is that the generated control torque is large, but the control accuracy is relatively low, and it is generally used in the attitude control of large spacecraft or agile spacecraft

[0005] In high-precision fast attitude maneuvering tasks, it is difficult to achieve good expected results by using RW or SGCMG alone

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