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kW of power was allocated for acceleration of plasma in the second part of the engine, via ion cyclotron resonance heating. To make that trip, about 60 metric tons of LOX-LH2 propellant would be expended. For instance, an empty OTV on the return trip to Earth covers the distance in about 23 days at optimal specific impulse of 5,000 s trabajos para trabajar en casa (50 kNs/kg) or in about 14 days at I sp of 3,000 s (30 kNs/kg).

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4 The second phase of the engine is a strong electromagnet positioned to compress the ionized plasma in a similar fashion to a convergent-divergent nozzle that compresses gas in traditional rocket engines. Retrieved February 27, 2010. . 12 VX-200SS edit In March 2015, Ad Astra announced the award of a 10 million award from nasa to advance the technology readiness of the next version of the vasimr engine, the VX-200SS (SS stands for steady state) to meet the needs of deep space. Archived from the original (PDF) on March 31, 2010. This section further heats the plasma to greater than 1,000,000 kelvin about 173 times the temperature of the Sun s surface. A significant portion of that 40 was waste heat (see energy conversion efficiency ). 2, contents, design and operation edit, vasimr schematic, vasimr, sometimes referred to as the Electro-thermal Plasma Thruster or Electro-thermal Magnetoplasma Rocket, uses radio waves 3 to ionize and heat the propellant, which is then accelerated with magnetic fields to generate thrust. "Projected Lunar Cargo Capabilities of High-Power vasimr Propulsion" (PDF). In particular, there is both overlap and disagreement between the selections and recommendations from nessie and cryptrec (as of the August 2003 draft report).

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