Magnetogyrogravitational system of three-axis orbital orientation and stabilization of the AUREOL-3 satellite

The problems of designing a satellite with the three-axis system of orientation and stabilization is discussed. Three types of mathematical models are presented: a complete nonlinear model of three dimensional motion, a nonlinear model of planar motion and a linear model describing motion as related to the mass centre of an axisymmetric satellite in all the basic operation regimes of the orientation system. The dynamics of the satellite motion is considered under the action of aerodynamic and gravitational moments as well as moments developed by the magnetic damper and flywheel. The parameters of the orientations system have been selected, the range of angular velocities and the angle providing transition of the satellite to the stabilization regime have been determined. The block diagram of the orientation and stabilization system is presented together with a description of the logics of their operation.