Abstract: The momentum envelope of fixed skew configuration control moment gyroscopes (CMGs) cannot be changed flexibly to meet the different satellite attitude maneuver requirements. The control method for variable skew configuration CMGs was designed. The dynamic model of the variable skew configuration CMGs was established. Considering multiple control variables, such as gimble rate, highspeed rotor speed and skew angle rate, the steer control law of the variable skew configuration CMGs was designed. The momentum envelope of CMGs and singular state distribution were analyzed. The variable skew configuration CMGs were used to achieve the satellite threeaxis attitude agile maneuver control. The simulation results show that the control method for the variable skew configuration CMGs can realize the satellite threeaxis attitude agile maneuver control with different number of CMG faults

Key words: control moment gyroscopes, variable skew configuration, momentum envelope, steer control law, attitude maneuver control