Abstract:

This paper studies the integrated power and attitude control of a spacecraft using variable speed control moment gyros (VSCMG). A globally asymptotically stable control law for attitude tracking is designed for a rigid body spacecraft with VSCMG as attitude control actuator. The angular velocities of gimbals and the angular accelerations of rotors are treated as a control input vector in the steering law design.

Key words: integrated , power , and , attitude , control,  , attitude , tracking,  , variable , speed , control , moment , gyro,  , energy , storage,  , configuration , singularity,  , wheel , speed , equalization