Pulsed Electromagnetic Thruster.
Final technical rept.,
TRW SYSTEMS GROUP REDONDO BEACH CALIF
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A pulsed inductive plasma thruster has been developed and its performance investigated experimentally. The thruster uses a 20 cm diameter coil through which current is pulsed by discharging a capacitor through a spark gap. Gaseous propellant is injected by a fast acting valve having a total open time of 200 microseconds. The mass utilization factor for this injector was 70 percent. The efficiencies determined by a thrust balance were lower than anticipated because of a large resistive dissipation. Author
- Electric and Ion Propulsion