ABSTRAKT

The motion of an artificial Earth satellite relative to its mass center is considered. For short-term disruption of operation of onboard sensors, which measure orientation angles and the absolute angular velocity, the dynamic Euler equation is supplementarily used in the algorithm for estimation of the mentioned parameters. Since actual and a priori data about the inertia tensor of the satellite and the external effects disturbing the motion can differ, the algorithm is provided by the property of robustness. The sets of potential values of the estimated parameters and external actions, which disturb angular motion of the satellite, are bounded by the corresponding ellipsoids.