AAWSAP DIRD, Aneutronic Fusion Propulsion II, November 2010

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capable of either generating low-thrust, high-specific-impulse exhaust or relatively
high-thrust, low-specific-impulse exhaust. The intention of the VASIMR design is to
bridge the gap between high-thrust, low-specific-impulse propulsion systems and low­
thrust, high-specific-impulse systems. AdAstra is currently testing the VX-200 engine (a
200-kW engine). The power distribution is as follows: A helicon discharge uses 30 kWe
(kilowatts, electrical}for ionizing the argon gas using RF waves and uses 170 kWe for
powering the ion cyclotron resonance to heat and accelerate plasma in the second part
of the engine. The specific impulse is optimally ~5,000 seconds, with a specific power
of ~1.5 kg/kW. The mass of the VX-200 engine is estimated at ~300 kg. NASA intends
to test this engine on the International Space Station using a large battery to power it
during the tests.
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