Single Gimbal Control Moment Gyro (SGCMG) is an effective actuator for three axis attitude control of satellites, which can generate higher torque than a reaction wheel. Utilizing the SGCMG system on satellites will make maneuver time shorter and energy consumption more efficient. It is required to reduce energy consumption during attitude maneuver because of limited energy supplies in space. This paper focuses on configuration of a pyramid type 4-SGCMG system, especially initial gimbal angles and pyramid skew angles which restrict the direction of the output torque. The effect of these angles on energy consumption will be clarified. The result of this study indicates that compared with the pyramid skew angle equal to 54.73 degrees which is adopted by number of studies for a spherical angular momentum envelope, the dispersion of energy consumption in each direction of maneuver is reduced by 63% when the skew angle is around 80 to 85 degrees.
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