Performances of an Argon Arc-Jet Thruster for Satellites
[ 1 ] Instytut Elektroenergetyki, Wydział Elektryczny, Politechnika Poznańska | [ P ] employee
2015
scientific article
english
- arc-jet
- space propulsion
- plasma flow modeling
EN Arc-jet thrusters are currently used for the propulsion of satellites. Low power arc-jet are functioning with propellant as helium, hydrogen, ammonia, lithium and argon. The performances such as axial thrust and specific impulse of a D.C. argon arc–jet are calculated by a fluid description of the arc with two kinetic temperatures (Te,T) and non equilibrium condition for the ionization. The electric input power is calculated from the conductivity which is deduced from plasma properties. The influence of different angles of the nozzle divergent part, arc current and mass flow rates on arc-jet performances is discussed. It is shown that the thrust is 0.3-2.5 N and the specific impulse 80-210 s for an argon mass flow rate 0.4-1.2 g/s and a arc current of 40-120 A.
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