MEMS-based propulsion with solid propellant for micro satellite

In this paper we develop a micro thruster of MEMS propulsion with solid propellant thruster responding to the spatial constraints and MEMS characteristics. The micro thruster has low power and energy thresholds for ignition and no moving parts, so they are expected to be highly reliable. Fabrication and assembly of array of 36 micropropulsion units proved the technological feasibility and the functioning performances. The electro-thermal process and gas dynamic characteristic of the micropropulsion is modeled and analyzed,. Eventually, a test platform is designed for micro-Newton second impulse bit. The initial test shows that the impulse is 4-11 μNs.