Study On The Gas Generating Technology For Solid Cool Gas Micro Thruster

This paper designed solid cool gas micro thruster suit for micro/nano satellite. It is composed of chamber, pressure sensor, valve and nitrogen generator.The cool gas generant was optimized by means of theoretical calculation which consists of NaN3 to be fuel and Fe2O3 to be oxidizer. The gas generating properties of the agent under different oxygen balance were characterized. It was indicated that the gas production and gas temperature rise with the oxygen balance decreasing. The agent reacts fast and the gas temperature is high at the oxygen balance of -5. NaN3 possesses the highest decomposition rate with low gas temperature when adding 0.05g Al/CuO thermite.The cool gas generant was optimized by adding LiF and Na2SiO3. The agent produces less impurities with low force capacity and covolume at the ratio of NaN3/LiF/Na2SiO3= 80%/10%/10%. Heating wire was used as the optimizing igniter. The wire consumes only 2W power with fast heating rate, and meets the igniting requirement at the diameter of 0.2mm. The nitrogen generator with the agents of 0.3g can produce gas at lower temperature accompanied with a higher gas generation rate.It was verified that the igniter could light the agents successfully by COMSOL Multiphysics numerical simulation, and the ignition delay was 2 seconds. In addition, the solid cool gas thruster properties were characterized by the torsion balance stand. Results show that the relation between impulse and chamber pressure linear function when chamber pressure varies from 0.15MPa to 0.5MPa.