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In this paper, the authors propose a new architecture for the control of the satellites’ attitude by using a control law mainly based on a proportional-integrator component with respect to the quaternion vector and to the satellite’s angular velocity vector. The control law has two nonlinear components with saturation zone; the actuators’ saturation will be considered both from the generated gyroscopic couples’ point of view and from the gyroscopic frame angular velocities’ point of view. The new obtained nonlinear control system is software implemented and validated through complex numerical simulations; the stabilization and the control dynamic characteristics of the system are obtained and analyzed in detail.

Nonlinear automatic control of the satellites by using the quaternion and the angular velocities’ vectors