• Relative Motion Control
• Moon Rendezvous
• Guidance Navigation and Control
• Control Constraints
• SDRE Control

This report presents the SDRE guidance and navigational technique with state constraints that is capable of driving a spacecraft approaching a target vehicle on Near Rectilinear Orbit in the Earth-Moon system. Nonlinear varying-time relative equations were used to design the guidance and navigation system. Comparison between controller based on elliptical and circular assumption for relative motion was done. Constraints and weight functions parameters are maintained as generic as possible, in a way to delineate a different requirements for the different missions. In order to fully validate the proposed solution, the Monte Carlo simulation has been performed over a range of 5 - 20 km for the relative position, in which the chaser can begin its rendezvous maneuvers even outside the cone. The results show that the performances, evaluated in terms of maneuvers time and fuel consumption, are comparable with real mission.