Three-axes attitude determination and control system based on magnetorquers for small satellites
Tutor / director / avaluadorCamps Carmona, Adriano José
Tipus de documentProjecte Final de Màster Oficial
Condicions d'accésAccés obert
This projects takes the desing and implementation of an attitude determination and control subsystem for the 3Cat-2 Mission. The system has to be able to correct the different perturbations and point the satellite to the desired orientation according to the working mode of the satellite. The subsystem has to be able to correct the different sensing perturbations and compute all the different attitude parameters to control the satellite. The design is divided in three different modes: Detumbling, Sun-safe, and Nominal. The Detumbling Mode is in charge of stabilizing the satellite rotation after the launch or when some other of the controllers has had a problem, and it induces a high rotation over the satellite. The Sun-safe is in charge of pointing the largest solar panels to the Sun to charge the batteries. Finally, the Nominal has to point the payload antennas to the Nadir (Earth Center) for performing the mission of the satellite. Each mode will make use of different sensors to save as much energy as possible. The work will be based on the usual algorithms used in different satellite mission and looking for a new and the first complex implementation of an Attitude subsystem for the Nanosatellite Laboratory.
In this TFM the attitude determination and control system for the 3Cat-2 nanosatellite will be implemented, including the sun sensors, 3 axes magnetometers and 3 axes gyroscopes to determine the satellite's attitude, and three axes magnetorquers as actuators. Algorithms will be tested in a Matlab-based simulation environment and then converted into C, to be executed in the Nanomind (on board computer) of 3Cat-2. Algorithm performance should be evaluated in an air bearing in the center of a 3 axes Helmholtz coils.