• extended linearization
• relative motion
• sdre
• sdre - H infinity
• space

Relative guidance algorithms for space applications were identified by NASA as an enabling technology for future missions development. Whenever two or more space vehicles must coordinate their motion or a terminal rendezvous has to be performed, a robust control of the relative motion occurring between the two objects is requested. Control must guarantee operation safety and minimize fuel consumption, since refuelling operations are currently too expensive. In this thesis, the extend linearization technique was adopted to design pseudo-optimal and robust control laws for nonlinear equations of relative motion. Typical perturbations of low Earth orbits were considered, in order to understand the feasibility of the developed controllers. Simulations were performed using data from real missions.