• electric propulsion
• Hall Thrusters
• TAL
• anode layer
• magnetic design
• scaling
• plasma thrusters

In recent times, there has been strong growth in the diffusion of Hall Thrusters, both as a main rocket propulsion system in deep space missions and for station keeping in Earth-orbiting satellites. The trend towards satellite miniaturisation poses the problem of reducing the size and power of such thrusters, where scaling down the ceramic walls is intrinsically difficult. The aim of this thesis is indeed the development of a 100 W Anode Layer Type Hall Thruster. There are a few examples in the literature, from which the thruster was scaled down. The scaling relations were adapted for this variant of thrusters by developing a model for wall and current utilisation losses while optimising the choice of the proper scaling modes. After the preliminary design was completed, the magnetic circuit was designed and optimised. This was done to obtain a magnetic field topology that maximises the thruster performances and operating life. The former via the maximisation of the field gradient and the latter by reducing the field lines entering the guard rings and moving externally the acceleration region. In turn, the topology was refined after coupling the magnetic analysis with the thermal model. Eventually, the anode was sized with the aim of simplifying the manufacturing process, while distributing uniformly the propellant flux entering the chamber in the azimuthal direction. Finally, a draft mechanical design was completed, and the thermal loads were evaluated to ensure proper safety margins.