Synthesizing analytical laws of spacecraft orbital attitude stabilization when attitude angle measurement data are unavailable

The paper proposes an approach providing a solution for the spacecraft orbital stabilization problem, which is described by a sixth order linear stationary model when measurements of all the attitude angles are not available. The derivation of the analytical solution is based on an original decomposition of the initial system model and the interrelation established in this work between modal control by state and modal control by output via specified values for the roots of the closed-loop control system. The proposed approach was used in order to synthesize laws for controlling orbital attitude, and the paper presents results of simulations for a hypothetical spacecraft.