• Control
• MPC
• Automation
• Aerospace

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.