In-space devices are rapidly increasing in number and variety. Although small spacecraft have already established a heritage, the industry is proving to be dynamic and evolving. Small sizes allow to achieve more efficient structures and consequently both lower costs and simpler designs. This thesis proposes a method to carrying out a close-range observe of a collaborative target with a CubeSat while performing a helix trajectory. The thesis objective is to devise a time-variant attitude maneuver to perform the observation, to choose a proper control solution and to build a model to test the solution and carry up a performance evaluation. To determine whether the design meets the re-quirements numerical simulations are carried out using Matlab and Simulink.