Model predictive control techniques for low-thrust spacecraft rendezvous

The first objective of this thesis is to present innovative MPC schemes, in which the cost function is defined by a sum of vector norms, instead of the typical quadratic one. This feature allows one to meet fuel optimization requirements which are typical of space applications. Closed-loop stability for both linear time-invariant and time-periodic systems is guaranteed by systematic methods to construct terminal cost and terminal constraints. Secondly, the proposed control schemes are applied to a variety of low-thrust autonomous space rendezvous missions, within an optimization-based framework. In particular, the scenarios addressed are: a long-range rendezvous on a near-circular orbit; a midrange mission involving periodic dynamics due to geopotential effects and solar eclipses; a halo orbit tracking mission. Another MPC strategy, which is able to account for mission-specific requirements, while satisfying on-off constraint inherent to the adopted EP technology, is presented. Finally, the trajectory planning problem for rendezvous and docking to a tumbling target is addressed. The use of a variable-horizon MPC strategy is proposed in order to construct an appropriate maneuver plan.