Fundamentals of 1 kW Hydrazine Arcjet Thrusters.
Final rept. 30 Aug 95-30 Jul 97,
ILLINOIS UNIV AT URBANA DEPT OF ELECTRICAL ENGINEERING
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This final technical report summarizes the research carried out by our group concerned with the fundamentals of hydrazine 1 kW arcjet thrusters. Section 1 presents modeling analysis that predict the nonequilibrium plasmadynamic processes by solving the two-dimensional, axisymmetric, chemical nonequilibrium viscous flows including heat transfer to the anode con-divergent nozzle. Section II presents the coupling of cathode sheath potential models necessary to account for the total voltage operating at 10 A. Excellent agreement is predicted to match data for a 1 kW hadrazine arcjet. Section III presents experimental studies of the internal anode sheath layer by utilizing an array of 14 electrostatic micro-probes. Axial and azimuthal distributions of such plasma properties as the floating potential, anode sheath potential, wall current density, electron number density and electron temperature are reported for powermass flow ratios ranging between 18 to 30 Mjkg. Excellent agreement between the data and the numerical models Sec I and II is found.
- Electric and Ion Propulsion