Abstract
Recent advances have been made in low-power (1 – 2 kW) arcjet performance with the aid of numerical, nonequilibrium plasma ow models. Consequently, validation of these models through experimentation has become increasingly important. We discuss diagnostic probe techniques for measuring the exit plane ow of a 1 kW class hydrazine thruster. A spatially resolved time-of- ight electrostatic probe method is described for measurements of radial pro les of the plasma axial velocity ui. These measurements are combined with previous quadruple probe measurements of Te and the ion speed ratio ui/cm to estimate the ion temperature Ti, resulting in Ti/Te ’ Tg/Te ; 0.4 at the thruster exit. The exit plane data for ui and Ti are compared with computational arcjet model predictions and previous experimental results, showing substantial agreement.
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