Modeling and implementation of Spacecraft Attitude disturbances and control systems in to a Satellite simulator
Correu electrònic de l'autorjuandavid.upcgmail.com
Tutor / director / avaluadorHyuk, Park
Tipus de documentTreball Final de Grau
Condicions d'accésAccés obert
In this project is wanted to create an attitude simulator to see how nanosatellites (particularly 1U CubeSats that are 10 x 10 x 10 cm of size) behave in front of external torques and perturbations, for instance solar pressure radiation torque, Earth oblateness perturbation and residual dipole moment between others, while orbiting in Low Earth Orbits (LEO). Simulator is based on Euler’s dynamics equations and from these equations is wanted to know the angular velocities that are caused due to external moments that are acting on the satellite. Euler equations have been numerically discretized by using 4th order Runge-Kutta. It guarantees a low discretization error than using other methods as the Euler that has more error. With this low error, we get high precision on simulations. Once total angular velocities are known, we use the Euler Angles representation to plot the roll, pitch and yaw because we are interested on seeing how much has our satellite turned. In simulations, we conclude that magnetic dipole moment is the one that has more impact on LEO missions for CubeSats. Also we see in the part of angles representation that satellite has a stable motion and periodic, this allow the use of active control on CubeSats without difficulty. Any active control is possible but for nano-satellites the most common are reaction wheels or magnetorques.