In this article, five feedback magnetic attitude control algorithms are compared in terms of stabilization accuracy and implementation problems. The control strategies are classic Lyapunov control with scalar gain; the same control strategy with matrix gain and a specific gain-tuning procedure; sliding control with a variable surface; a linear quadratic regulator constructed for a special time-invariant system of a higher degree than the initial time-varying system; and a special controllable trajectory developed using particle swarm optimization. A new sliding surface construction method is proposed in this paper. Surface parameters were changed in every control iteration to ensure that the required control torque component along the geomagnetic induction vector was small. The advantages and drawbacks of the considered methods and their applicability for different target attitudes are discussed.

This paper considers a construction procedure of a satellite reference angular motion in the vicinity of an unstable gravitational equilibrium position. The satellite is stabilized on the reference trajectory by the magnetic coils. The problem is solved in several stages. An optimization problem to be solved by the particle swarm optimization method is formulated at each stage. Cost functions are based on the linearized model analysis. The main stage is the construction of a special reference motion, which provides the minimum control torque projection on the geomagnetic induction vector. Optimal geomagnetic field dipole approximation for a given time interval is considered to reduce tracking errors. The paper compares combinations of different cost functions in terms of the terminal attitude accuracy in the presence of perturbations.

The three-axis magnetic control for satellite angular motion is considered. The control torque cannot be applied along the geomagnetic induction vector. The system is ultimately controllable. However, the control construction or its parameters adjustment require specific procedures. Biologically inspired optimization algorithm is proposed to find the feedback control gains that accommodate the disturbances influence.

The paper describes how to solve the problem of the orbit correction thrusters’ distribution on board the geostationary satellite. It is necessary to simultaneously correct orbital parameters, which means to change the characteristic velocity in the local horizon plane, and provide reaction wheels desaturation. Moreover, the paper determines the required number of thrusters, providing the system operability even if one thruster fails.