Propulsive landing is one of the most promising technologies for reuse of orbital launch vehicles. This master thesis presents a concept of guidance and control systems for recovery of a first stage booster of a 1 ton to Low Earth Orbit capable launch vehicle. Two different trajectory scenarios were tested in a six degrees of freedom simulation environment which also included realistic wind disturbances. With a dispersed initial position, the rocket stage was able to land reliably within the landing pad constraints. When using realistic wind data, the probability of a successful landing decreased, and a wind speed constraint had to be imposed on the mission criteria.