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.