Synthesis of Control Algorithms of the Spacecraft Spatial Reorientation with the Use of Dynamic Equations of a Solid Body Rotational Motion in Rodrigo-Hamilton Parameters

摘要

An algorithm for SC spatial reorientation in a specified time interval is presented. In contrast to the classical formulation the traditional restrictions are not imposed on the class of spacecraft angular motions. The proposed approach based on the maximum principle allows one to obtain an analytical solution of the problem of optimal spatial reorientation of the spacecraft. On the basis of the proposed algorithm software for the mode of spacecraft "Egyptsat-l" and "Sich-2" rotations has been implemented.