Attitude control of small satellite based on single gimbal control moment gyroscope

Abstract

Control Moment Gyroscope is being used for attitude control of spacecraft. Their torque producing mechanisms help the modern spacecrafts to achieve their operational goals. Focus is made on single gimbal control moment gyroscope which produce torque in relation to the angular momentum of the rotating wheel and the rate at which the wheel is tilted. Fast slew rates and greater torque are required for the spacecrafts to have better transmission and usefulness. The SGCMG ingrained higher output torque that makes it significantly functional for the spacecraft with high slew rate requirements. This research incorporates rotational dynamics of hardware modelling. Hardware development of single gimbal control moment gyroscopes being carried out and one axis orientation control is obtained.