  This work deals with an ADCS model for a satellite orbiting around Earth. The
object is to achieve a preliminary design and perform some analysis on it. To
do so, a GNB was selected and main properties are exploited. Previous works of
[9], [13], [14], [15] and [17] were analyzed and a synthesis was obtained; then
a suitable control system was designed to satisfy technical requirements.
Coding was performed using Matlab and Simulink.
  Keywords: Attitude Determination, Attitude Control, Nanosatellite, Orbital
Perturbations, Quaternion, Two Body Problem, Euler's Equations, Lyapunov
Function.
