Orbit and attitude simulation of nanosatellite for attitude motion analysis under the influence of perturbation forces
Keywords:
Low Earth Orbit, Nanosatellite, Orbital Motion, Orbital SimulationAbstract
This work describes the construction of a simulation of the low Earth orbit (LEO) trajectory of a nanosatellite, as well as its attitude under the influence of the most significant perturbation forces. The entire simulation environment was implemented in Matlab/Simulink. The orbital trajectory was developed using classical equations without considering drifts. For attitude, disturbance torques were included due to gravity gradient, geomagnetic field, residual atmospheric drag force, and solar pressure. The results showed a good environment for studying attitude in LEO, which will allow analysis of future attitude determination and control systems.
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