The second phase of the engine is a strong solenoid-configuration electromagnet that channels the ionized plasma, acting as a convergent-divergent nozzle like the physical nozzle in conventional rocket engines.Ī second coupler, known as the Ion Cyclotron Heating (ICH) section, emits electromagnetic waves in resonance with the orbits of ions and electrons as they travel through the engine. By varying the amount of RF heating energy and plasma, VASIMR is claimed to be capable of generating either low-thrust, high–specific impulse exhaust or relatively high-thrust, low–specific impulse exhaust. On entering the engine, the gas is first heated to a "cold plasma" by a helicon RF antenna/coupler that bombards the gas with electromagnetic energy, at a frequency of 10 to 50 MHz, stripping electrons off the propellant atoms and producing a plasma of ions and free electrons. The propellant, a neutral gas such as argon or xenon, is injected into a hollow cylinder surfaced with electromagnets. Other related electrically powered spacecraft propulsion concepts are the electrodeless plasma thruster, the microwave arcjet rocket, and the pulsed inductive thruster. The resulting plasma is then accelerated with magnetic fields to generate thrust. In these engines, a neutral, inert propellant is ionized and heated using radio waves. VASIMR is a type of electrothermal plasma thruster/electrothermal magnetoplasma thruster.
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