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With the improvement of remote sensing satellite observation capability, agile satellites with rapid mobility have attracted increasing attention. In order to realize the high pre-cision earth observation and stereo imaging in the same orbit, the earth observation satellite needs to have the ability of fast attitude maneuver and stabilization. The satellite needs to have the ability of fast attitude maneuver to track the target. In order to realize the fast attitude maneuver of agile satellite, the Pentagon configuration composed of six SGCMGs is used as the attitude control actuator. In order to shorten the time required for attitude maneuver of satellite, the angular trajectory of attitude maneuver around Euler axis is planned, and the error quaternion between the actual attitude and the planned attitude of satellite is calculated. Variable structure control law is designed with error angular velocity. The simulation results show that the control law designed in this paper can effectively complete the attitude maneuver around the Euler axis and has strong robustness.

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