FIGURE 1-8. Simplified schematic diagram of arc-heating electric rocket propulsion system. The arc plasma temperature is very high (perhaps 15,000 K) and the anode, cathode, and chamber will get hot (1000 K) due to heat transfer.
(1000 to 50,000 m/sec). There are many different types and geometries. A simple pulsed (not continuously operating) unit with a solid propellant is shown in Fig. 1-10. This type has had a good flight record as a spacecraft attitude control engine.
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