On the rapid orbital attitude control of manned and cargo spacecraft Soyuz MS and Progress MS

Abstract

An algorithm for the rapid construction of the orbital coordinate system (OCS) used in the control system of the manned and cargo spacecraft Soyuz MS and Progress MS is considered. The algorithm is used to speed up the current determination of the state vector value using the satellite navigation equipment immediately after the spacecraft is placed into the Earth’s artificial satellite orbit and the launch vehicle is separated. The proposed algorithm is based on an a priori knowledge of the launch vehicle’s attitude parameters at the time of separation and on the angular velocity (AV) measurements available on board after the start of the strapdown inertial navigation system (SINS). The efficiency of the rapid orbital attitude control algorithm is confirmed by the results of the mathematical modeling and flight development tests.