The dynamics of the spacecraft control with the biaxialgyrodyn on the base of the three-degree-of-freedom gyroscopes and the dynamics of the uniaxial gyrodyn on the base of the two-degree-of-freedom gyroscope is shown in the article. The dynamics of the gyrodyns and the process of the spacecraft controlling is described on the base of the theory of the three-degree-offreedom astatic gyroscope. The equations of the motion are made on the base of the kinetostatics method. The analysis of the gyro-dyndinamicsis carried out on the base of the solution of differential equations, describing the gyrodyn dynamics. It is shown, that if one uses the gyrodyns on the base of the two three-degree-offreedom gyroscopes, the system "spacecraft-gyrodyn" has the guided turn of the spacecraft which eliminates its angle of list andangle of pitch deviation. To carry out the spacecraft course angle control one needs for another biaxial gyrodyn. There is shown that the guided turn of the spacecraft is accompanied with the high-frequency oscillations of the system "spacecraft - gyrodyn'' relatively the coordinates offset. The dynamics of the uniaxial gyrodyn based on the two-degree-of-freedom gyroscopeis investigated subject to the elasticity of the bearing assemblies, backlash in the reducer of the gyroscope bracket drive, the dynamics of the drive electric motor. The analytical dependence for the calculation of the velocity of the gyrodyn turn through the given angle relatively the axis of its bracket was received. The analysis of the dependence of the velocity of the bracket rotation on the gyrodyn parameters was carried out. It is shown, that the transient of the bracket rotation velocity is accompanied with the high-frequency damped oscillations with the minor amplitude. The article material could be used while the creation of the training courses in the academic subject "The systems of the movement control and navigation".