Performance analysis and experimental research on nitrous oxide monopropellant micro-thruster
Sun Wei1, Fang Jie1, Cai Guobiao1, Cong Yu2*
1. School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
2. Laboratory of Catalysts and New Materials for Aerospace, Dalian Institute of Chemical Physics, Dalian 116023, China
Performance analysis for monopropellant micro-thruster using nitrous oxide (N2O) propellant was carried out based on the thermodynamic computation. Preliminary results show that decomposition rate of nitrous oxide and the expansion ratio of nozzle both have effects on the specific impulse of the thruster. Experiments of nitrous oxide catalytic decomposition at different initial catalyst bed temperature were conducted in testers of different structures. Self-sustaining decomposition reaction of nitrous oxide was observed at preheated temperature of 250�ݡ�. The performance of the sub-Newton micro-thruster was greatly affected by the combustion chamber structure and the loading factor of catalyst bed according to experimental results. Although the results are not conclusive because of the small initial test set, preliminary numbers demonstrate the feasibility of the N2O monopropellant micro-thruster.
Sun Wei, Fang Jie, Cai Guobiao, Cong Yu.Performance analysis and experimental research on nitrous oxide monopropellant micro-thruster[J] JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2008,V34(12): 1469-1472