Abstract: Gyrowheel has the advantage of small size, light weight by its high level of system integration, and it has been attempted to be applied in micro-satellite attitude control system. A linear dynamics model of GyroWheel was built, and then pole-zero analysis was carried out to obtain its basic dynamic characteristics which is different with dynamic tuned gyros (DTG). It is indicated that gyrowheel has two feature frequencies in addition to the precession and nutation frequencies outside. The correctness of the analytical model is proved by the ADAMS model and its simulation. The controlled object characteristic analysis foundation is so provided for gyrowheel to be applied in the attitude control system.

Key words: GyroWheel, spacecraft attitude control system, second harmonic torque items, pole-zero analysis