Abstract: A modeling analysis is given to investigate the plasma flow and heat transfer of lowpower (kW class) archeated thrusters (arcjets). The hydrogen/nitrogen mixtures are chosen as the propellants to simulate decomposed ammonia and hydrazine. The temperature and velocity distributions in the arcjets with different inlet pressures and arc currents are presented. The modeling results show that with the increase of the arc current, the temperature along the axis increases, and the velocity at the exit plane and the specific impulse also increase. With the increase of inlet pressure, the mass flow rate and velocity at the center of nozzle exit also increase. A numerical simulation is carried out for the NASA 1kW class arcjet thruster, and the results are almost consistent with the available experimental data.

Key words: arcjet, flow and heat transfer, numerical modeling