International Journal of Aerospace Engineering / 2013 / Article / Fig 8

Research Article

Experimental Investigations of a Krypton Stationary Plasma Thruster

Figure 8

ATON A-3 (a) current-voltage characteristics of the discharge and the dependences of (b) the thrust, (c) anode efficiency, and (d) specific impulse on the discharge voltage at the anode mass flow rate of 2.3 mg/s in operation on Kr, optimized model (purple square ▪), and Xe (blue triangle ▴).

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