The main objective of this work consists in the design of a damping system for a plasmatic thruster used in aerospace applications and, in particular, for the propulsion of satellites. In particular, the following study deals with systems with non-linear dynamics. The adopted method was to develop all the solutions found in parallel, deciding whether to deepen them or abandon them when they are evaluated as potentially non-functional. For each damping system, the following phases were pursued: the study of physical principles and dissipation mechanisms, design and planning of solutions and their components, model simulation, fabrication and experimentation with subsequent data analysis.