Design and development of a fluid system for a resonant igniter

The purpose of this thesis is the design process and development of a proper fluid system dedicated to supply a resonant igniter for use in satellite and upper stage propulsion applications. First of all, an overview of the main characteristics and fundamentals of resonance ignition is pointed out. Following this, a first test campaign is analysed with regards to the main parameters affecting resonance ignition. Secondly, according to experimental results and igniter design data, a blowdown calculation model for the fluid system design and sizing is presented. Particular attention is paid on assumptions taken and equations used in order to dimension blowdown tanks. Afterwards results of a blowdown test campaign conduced are considered, aiming to validate the calculation model previously addressed. Thank to this an improved model is obtained, with whom the final fluid system blowdown tanks are designed. Furthermore the tanks filling issue is discussed. Finally, considering resonance ignition future improvements, a possible integration solution of the designed fluid system in a spacecraft is proposed.