One of the most essential tasks of a satellite is to point an instrument along a desired direction in order to achieve mission requirements. In many cases, this operation is complicated due to the presence of sensitive on-board instruments, which cannot be pointed along certain directions, such as the Sun or other bright objects. This problem can be analyzed as a reorientation problem in the presence of attitude constraints. In literature there are not many research papers that address the constraints problem, and its solution has great importance for practical scientific missions. In this thesis work, a guidance algorithm based on the Artificial Potential Field method is analyzed and implemented in MATLAB/Simulink environment, which allows us to describe the desired pointing and the restricted areas through potential fields.