Preliminary scoping studies for nozzle-based coaxial plasma thrusters

Details Preliminary scoping studies for nozzle-based coaxial plasma thrusters Preliminary scoping studies for nozzle-based coaxial plasma thrusters

Jan 1991

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1991aipc..217..493g&link_type=abstract

Proceedings of the eighth symposium on space nuclear power systems. AIP Conference Proceedings, Volume 217, pp. 493-500 (1991).

Computer Science

Performance

Lunar, Planetary, And Deep-Space Probes, Propulsion Reactors

Scientific paper

The ideal steady-state properties of nozzle-based coaxial plasma guns are modelled by means of a magnetic Bernoulli equation. Formulas for thrust, power usage, mass flow rate, and specific impulse using hydrogen are thereby obtained, and are used to approximately assess the mission performance capabilities of such thrusters. Parameters in the range of experience of the Los Alamos spheromak group are addressed within the context of orbit raising, slow (cargo) missions to mars, and fast missions to mars. The various internal atomic and plasma effects on hydrogen plasma thruster performance are approximately estimated or bounded. It is concluded that such devices may be relevant to mission performance at reasonable power levels.

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