Method of equivalent transformations to control an observation satellite by means of inertial drives under uncertainty

A system of differential equations for the angular motion of an observation satellite (OS) equipped with an inertial drive electromagnetic device (EMD) without a controlling flywheel engine is presented. Apart from lag, the calculated and uncertain limited external and parametric disturbances constantly acting on the OS control system are taken into account. It is proposed that the sliding conditions be used to obtain the high-precision OS control with the specified direct indices of the transient process quality in the angular motion. A problem of equivalent system transformation is solved to safely provide the invariance of the sliding conditions to all listed disturbances with respect to the Euler angles and their first and second derivatives.