Nutational oscillations suppression in attitude dynamics of spacecraft by relative motion of its movable module

Abstract

Attitude dynamics of a spacecraft with a movable module on retractable beams are considered. The movable module is attached to the main body of the spacecraft by retractable beams of variable length. The spacecraft main body contains a simple jet-engine with constant thrust. The retractable beams can tilt the movable module relatively the main part of the spacecraft, which shifts the position of the mass center. The control scheme of the nutation oscillations suppressing is constructed. This control scheme uses the impulses of the jet-engine on intervals of positive values of the equatorial component of the spacecraft angular velocity at the constant angular displacement of the movable unit. The main aim of this work is to develop the simplest control algorithm, which can be applied in cases of simple constructional forms of the small spacecraft with primitive equipment, including nano-satellites, that is economically profitable and can be used in more space missions.