Generally the objective of the attitude determination and control system (ADCS) is to stabilize the spacecraft. It has to react to all disturbances resulting from the environment in the low-earth orbit (LEO). Also the ADCS should be able to reorient the spacecraft into a predetermined attitude, thus providing controllability to high extend.
The requirement for our mission is to orient the CubeSat’s role axis “z” in the flight direction with an accuracy of +/- 20°, because of the maximum drag of the sail in this position. Additionally it is desirable to have an angular velocity as low as possible. To achieve these goals, the ADCS uses sun sensors and magnetometers to determine the satellite’s position in the earth orbit. For the attitude control, this system will use air core coils as magnetorquers.