Implementação de um simulador para o controle de atitude em nanossatélites
This work presents an attitude control simulator for nanosatellites which comprises a navigation system (attitude estimator) and a Proportional Derivative (PD) controller. The sensors used to estimate the attitude were composed of a magnetometer and a solar sensor, simulated by an ideal model wit...
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| Formato: | Dissertação |
| Idioma: | por |
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Brasil
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| Endereço do item: | https://repositorio.ufrn.br/jspui/handle/123456789/26344 |
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| Resumo: | This work presents an attitude control simulator for nanosatellites which comprises
a navigation system (attitude estimator) and a Proportional Derivative (PD) controller.
The sensors used to estimate the attitude were composed of a magnetometer and a solar
sensor, simulated by an ideal model with the addition of white noise. For the dynamic
equations the nanosatellite is considered to have a rigid body and to describe the kinematic
equations, quaternion was chosen. Within the navigation system, the norm-constrained
Extended Kalman Filter has been proved to be adequate to estimate the angular velocity
and its attitude using the sensors embedded into the nanosatellite. Different tests have
been performed to validate the simulator, the navigation system and the PD controller.
The results demonstrate that the set up is capable of stabilizing and correcting the attitude
of the nanosatellite even in the presence of different perturbations, large angles and high
angular velocities. Thus, the developed simulator presented adequate results, allowing it
to be used in future nanosatellite studies. |
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