Feasibility Study of a Hybrid Thruster using Wire-Shaped Magnesium and Water for Application to Small Spacecraft

High thrust propulsion systems that can be used in small spacecraft are urgently needed to expand the use of spacecraft. This study proposes a hybrid thruster for using wire-shaped magnesium as fuel and water an oxidizer. “Hybrid thruster” means in-space system generates chemical reaction between solid vapor oxidizer, such those utilized rockets. Both very safe, highly available, storable. To assess feasibility thruster, we carried out experiments utilizing magnesium-wire combustion at pressure lower than atmosphere, estimated input power ignition, ignitability, average mass consumption rate. Then, performances were calculated experimental results, which show there is 2–3 W, with higher ignitability rate thinner wires. The specific impulse achieved its maximum 323 s, mixture ratio 1.25. At ratio, wires having diameters 0.5 mm 0.8 was 49.8 mN 68.5 mN, respectively. Additionally, applicability shown through case considering existing deep-space misson.