The picosatellite UWE-3 is the third generation of CubeSats at the University Würzburg. It is equipped with all necessary satellite systems, among them the attitude determination and control system (ADCS), which will enable the satellite to determine its own orientation in space and, within its actuator capabilities, to control and change this attitude. The work described in this thesis report is focussed on the attitude control part of the ADC system, which is based on magnetic torquers and a miniature reaction wheel. The design, manufacturing and implementation of the magnetic control actuators for UWE-3 will be described, as well as experiments and tests of both actuator systems in combination with dierent control algorithms. Therefore, an attitude control test setup for picosatellites has been designed and manufactured in the context of this work. Additionally, simulations have been performed to verify the functionality of dierent control strategies under various conditions.