The paper considers a spacecraft moving in a circular near-Earth orbit with arbitrary inclination in the magnetic and gravitational fields of the Earth. The spacecraft is equipped with an electrodynamic control system for attitude stabilization, which generates Lorentz and magnetic control torques. The process of spacecraft stabilization in an indirect position is studied, taking into account an unknown small disturbing torque, spacecraft position data, etc. The problem is to select the gain coefficients of the control torques, which are determined using particle swarm optimization (PSO), taking into account the spacecraft parameters, orbit, and initial data on the attitude position and angular velocity of the spacecraft. The problem is solved without restrictions on the order of accuracy of the geomagnetic field model. The results of numerical experiments demonstrating the operability of the proposed control are presented.