Implementation of the Orbital Orientation Mode of an Artificial Satellite of the Earth without Accumulation of the Angular Momentum of the Gyro System

Abstract

We consider the motion of an artificial satellite of the Earth of the Progress and Foton-M4 type in different variants of the orbital orientation mode in low Earth orbit. A gyro system (a set of reaction wheels or control moment gyros) is used as the executive part of the satellite control system. The gravitational and restoring aerodynamic torques acting on the satellite are taken into account. Based on the principles of the proportional-differential regulator, we construct the control laws for the gyrostatic momentum, which allow, without its accumulation, maintaining a long and sufficiently accurate orientation of the satellite in the vicinity of gravitationally stable and unstable rest positions that exist in the simplified problem (the satellite moves in a fixed circular orbit under the action of the gravitational torque only; the gyrostatic momentum is zero).