International Journal of Aerospace Engineering / 2013 / Article / Fig 7

Research Article

Experimental Investigations of a Krypton Stationary Plasma Thruster

Figure 7

ATON A-3 anode efficiency versus discharge voltage for propellant anode mass flow rate of 2.3 mg/s: operation on Xe (yellow triangle ▴); operation on Kr (purple square ▪), optimized model; operation on Kr (blue diamond ♦), non optimized model.

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