The physics and engineering of the VASIMR engine

Chang‐Diaz, Franklin; Squire, Jared P.; Bengtson, Roger D.; Breǐzman, B. N.; Carter, Mark; Baity, F. W.

doi:10.2514/6.2000-3756

Cited by 42 publications

(15 citation statements)

References 2 publications

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“…In addition, there are other thruster concepts, such as the VAriable Specific Impulse Magnetoplasma Rocket (VASIMR) [39], that may be suited for this mission. The VASIMR is a two-stage plasma propulsion device: the production of the plasma is accomplished in the first stage, and the heating and acceleration in the second.…”

Section: Other Viable Candidatesmentioning

confidence: 99%

A Survey of Propulsion Options for Cargo and Piloted Missions to Mars

Sankaran

Cassady

Kodys

et al. 2004

Annals of the New York Academy of Sciences

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Section: Other Viable Candidatesmentioning

confidence: 99%

A Survey of Propulsion Options for Cargo and Piloted Missions to Mars

Sankaran

Cassady

Kodys

et al. 2004

Annals of the New York Academy of Sciences

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“…These claims may have been optimistic since heat rejection technology was perhaps overestimated and turbine materials to withstand such high temperatures have yet to be proven. Currently available commercial gas turbine technology allows turbine inlet (firing) temperatures of 1,700 K. 10 On the other hand, commercial SiC coated UCO and UO 2 particle fuel has been amply demonstrated to have typical operating temperatures of 1,473 -1,523 K. 11 No significant fission product release was seen in elevated temperature tests for periods up to 500 hours at 1,873 K for either fuel. ZrC coated UC 2 particle fuel was designed for operation at 3,200 K for 7 hours and should be able to achieve a sustained operating temperature up to 2,100 K, though that has not been conclusively proven.…”

Section: Nerva Derivativementioning

confidence: 99%

Multi Megawatt Power System Analysis Report

Longhurst¹,

Harvego²,

Schnitzler³

et al. 2001

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Missions to the outer planets or to near-by planets requiring short times and/or increased payload carrying capability will benefit from nuclear power. A concept study was undertaken to evaluate options for a multi-megawatt power source for nuclear electric propulsion. The nominal electric power requirement was set at 15 MW e with an assumed mission profile of 120 days at full power, 60 days in hot standby, and another 120 days of full power, repeated several times for 7 years of service. Of the numerous options considered, two that appeared to have the greatest promise were a gas-cooled reactor based on the NERVA Derivative design, operating a closed cycle Brayton power conversion system; and a molten lithium-cooled reactor based on SP-100 technology, driving a boiling potassium Rankine power conversion system. This study examined the relative merits of these two systems, seeking to optimize the specific mass. Conclusions were that either concept appeared capable of approaching the specific mass goal of 3-5 kg/kW e estimated to be needed for this class of mission, though neither could be realized without substantial development in reactor fuels technology, thermal radiator mass efficiency, and power conversion and distribution electronics and systems capable of operating at high temperatures. Though the gas-Brayton systems showed an apparent advantage in specific mass, differences in the degree of conservatism inherent in the models used suggests expectations for the two approaches may be similar. Brayton systems eliminate the need to deal with two-phase flows in the microgravity environment of space.iii CONTENTS

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“…The Variable Specific-Impulse Magnetoplasma Rocket [1,2] (VASIMR R ) is an in-space advanced electric propulsion rocket being developed by the Ad Astra Rocket Company (Houston, Texas, USA). It uses strong magnetic fields to contain and direct a high-power plasma for high-specific impulse propulsive thrust.…”

Section: Introductionmentioning

confidence: 99%

Inverse estimate of heat flux on a plasma discharge tube to steady-state conditions using thermocouple data and a radiation boundary condition

Faoite¹,

Browne²,

Gamboa³

et al. 2014

International Journal of Heat and Mass Transfer

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The heat flux incident upon the inner surface of a plasma discharge tube during a helicon plasma discharge was estimated using an inverse method. Temperature readings were taken from the outer surface of the tube using thermocouples, and the temperature data were interpolated over the tube surface. A numerical inverse procedure based on the Alifanov iterative regularisation method was used to reconstruct the heat flux on the tube inner surface as a function of space and time. In contrast to previously-used inverse models for this application, the current model implements a thermal radiation boundary condition to realistically model the energy exchange in the device. Additionally in these experiments, steady-state operation was reached, and the accurate modelling of the steady-state condition was facilitated by the thermal radiation boundary condition. The variation of heat flux with helicon discharge power, propellant flowrate, and electromagnet current was studied, and it was found that the waste heat flux increased with applied RF power and propellant flowrate, and decreased with current supplied to the electromagnets, over the range of parameter variation tested.

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The physics and engineering of the VASIMR engine

Cited by 42 publications

References 2 publications

A Survey of Propulsion Options for Cargo and Piloted Missions to Mars

A Survey of Propulsion Options for Cargo and Piloted Missions to Mars

Multi Megawatt Power System Analysis Report

Inverse estimate of heat flux on a plasma discharge tube to steady-state conditions using thermocouple data and a radiation boundary condition

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