Abstract:

This investigation is concerned with the modeling and dynamic analysis of a spacecraft comprising a rigid platform and a given number of double-gimbal control moment gyroscopes for high-precision attitude control. The equations of motion are derived by a Lagrangian approach using quasi-coordinates. Especially, coordinates of outer-gimbal, inner-gimbal and rotor are chosen to be principal-axis frames and angular momenta about them are all taken into account. The particular but compact model of attitude dynamics is concluded using helpful signs.

Key words: satellite,  , attitude , control,  , doublegimbal , control , moment , gyroscope,  , Lagrangian , equations,  , servo , system