Measurement and Control Integration Method of Spacecraft Attitude Based on MSCMG

Torque of the magnetic suspended rotor in a magnetically suspended control moment gyroscope (MSCMG) is caused by the spacecraft motion, rotation of the gyroscope frame, and relative motion of rotor. The rotor torque size is determined by magnetic bearing force only. At the same time, MSCMG introduces the elastic supporting magnetic bearings with clearance and active controllability. Rotary spindle of magnetic suspension rotor can be deflected with the angular velocity in the magnetic gap range, and thus output torque of the micro framework. Therefore, in a MSCMG, the magnetic bearing reference coordinate system coincides with the body coordinate system installation. The frame is motionless, and the spacecraft moves in only one direction. Through measuring magnetic bearing control current and rotor deflection displacement information, spacecraft attitude angular velocity and the angular acceleration in single direction can be obtained by using expression of magnetic suspension rotor radial torque caused by spacecraft motion. And through the torque of micro framework in rotor, high-precision control of spacecraft attitude in single direction can be realized. The simulation results show that this method can achieve measurement and control integration in single direction, and can meet the requirements of high precision control.