PURPOSE: To keep the attitude and its variation speed of artificial satellite always in desired conditions, by compensating the attitude change and its inertial motion due to the air lift at a low altitude region.

CONSTITUTION: Observing unit 9 calculates the observed value of attitude of satellite from the inputs of solar angle and terrestrial angle measured by earth sensor and sun sensor, and attitide condition presuming unit 10 calculates the attitude and its variation speed at the instant from the input of the above observed value. On the other hand, control command computing unit 11 calculates predictive value of the variation speed of desired attitide at a desired instant. Further, controllable manipulated variable computing unit 13 calculates, from the output of units 10 and 11, controlled variables necessary for obtaining agreement between attitide variation speed at the present instant and the attitude and its variation speed at the desired instant. Computor 14, arranged as above, affords these controlled variables to wheel driving circuit 7, where torque is genetated for achieving attitude control of the artificial satellite.