Sistema de Controle de Atitude de Satélites Utilizando Dispositivos de Troca de Momento Angular

In this work, the attitude control system on a 1U CubeSat is performed using a non-linear system, developed from the use of momentum exchange devices. The methodology considers two axes of rotation per actuator, being them the main and gimbal axis. The system based on speed control obeys the Lyapunov stability conditions and its behavior is evaluated under maneuver and perturbations, obtaining an accommodation time of 0.38% of the orbital period and a maximum variation of 0.032% in relation to the desired quaternions under the application of the maximum supported torque before the saturation of the actuators.