Prospects for nuclear electric propulsion using closed cycle magnetohydrodynamic energy conversion

Litchford, Ron J.; Bitteker, Leo; Jones, Jonathan E.

doi:10.2514/6.2001-961

Cited by 26 publications

(12 citation statements)

References 10 publications

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“…Therefore, there is a minimum radiator mass in radiator temperature (Figure7.). And compressor mass increase proportion to a increase of compressor power due to an increase of mass flow rate 4 . As a result, influence on radiator mass and compressor, system mass and specific mass have minimum point in radiator temperature.…”

Section: B Radiator Temperaturementioning

confidence: 99%

“…Master student, Nagaoka University of Technology, Non-AIAA Member 2 Assistant Professor, Nagaoka University of Technology, Non-AIAA member 3 Associate Professor, Nagaoka University of Technology, Non-AIAA member 4 Associate Professor, Nagaoka University of Technology, Non-AIAA member 5 Professor, Nagaoka University of Technology, AIAA Senior Member, nob@nagaokaut.ac.jp …”

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confidence: 99%

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Study on Specific Mass of Nuclear Electric Propulsion System with Closed Cycle MHD Generator

Miyazaki

Takahashi²,

Sasaki³

et al. 2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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In space, radiation dose to crew increases in proportion to a increase of flight-time. High radiation dose to human have an influence on human health. Therefore, propulsion system that can minimize in-flight time is required. In the present study, to minimize in-flight time, nuclear electric propulsion system (NEP system) is suggested for human exploration to Mars. NEP system consists of CCMHD power generation system driven by nuclear fission reactor (NFR) providing electric power to the propulsion system and the variable specific impulse magneto-plasma rocket (VASIMR ® ). In this study, modeling of power plant for NEP system and system analysis of it is carried out. Then Parameter are changed, the outlet temperature of NFR, the radiator temperature and the enthalpy extraction of MHD generator, in order to know how to minimize specific mass In the outlet temperature of NFR change, specific mass of NEP system decreases with an increase of outlet temperature of NFR. In the radiator temperature change, specific mass of NEP system have minimum point in radiator temperature. In the enthalpy extraction of MHD generator, specific mass of NEP system have minimum point in enthalpy extraction. Specific mass of NEP system less than ] / [ 2 kWe kg system   could be expected. Nomenclature system  = specific mass of the propulsion system rad  = mass per unit area of the radiator  = specific heat ratio  = emissivity of radiator  = the Stefan-Boltzmann constant co  = isentropic efficiency of compressor MHD  = isentropic efficiency of MHD generator rad A = radiator area . .E E = enthalpy extraction of MHD generator p C = specific heat m  = mass flow rate of working medium n = compressor number ico P = inlet pressure of compressor 2 iMHD P = inlet pressure of MHD generator oco P = outlet pressure of compressor oMHD P = outlet pressure of MHD generator eMHD Q = electric power from MHD generator ex Q = exchange power in regenerator ico Q = inlet thermal power of compressor ilre Q = inlet thermal power of low temperature side of compressor iMHD Q = inlet thermal power of MHD generator oco Q = outlet thermal power of compressor ohre Q = outlet thermal power of high temperature side of compressor oMHD Q = outlet thermal power of MHD generator or Q = outlet thermal power of nuclear thermal reactor rad Q = waste thermal power from radiator wco Q = compressor power ex T = temperature difference in regenerator iMHD T = inlet temperature of MHD generator ihre T = inlet temperature of high temperature side of compressor olre T = outlet temperature of low temperature side of compressor oMHD T = outlet temperature of MHD generator or T = outlet temperature of nuclear thermal reactor rad T = radiator temperature rad M = radiator mass system M = NEP system mass pro Q = thermal power of propulsion system

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Section: B Radiator Temperaturementioning

confidence: 99%

mentioning

confidence: 99%

Study on Specific Mass of Nuclear Electric Propulsion System with Closed Cycle MHD Generator

Miyazaki

Takahashi²,

Sasaki³

et al. 2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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“…2,3 The CCMHD electrical power generator has several advantages, that is, virtually no upper limits to the temperature it can tolerate, rapid response, and the ability to achieve high thermal efficiency and power density, 4 which lead to a reduction of the system specific mass. Despite such great advantages, the MHD generator is still subject to unstable nonequilibrium plasma behavior due to ionization instability.…”

Section: Suppression Of Ionization Instability In a Magnetohydrodynammentioning

confidence: 99%

Suppression of ionization instability in a magnetohydrodynamic plasma by coupling with a radio-frequency electromagnetic field

Murakami

Okuno

Yamasaki

2005

Applied Physics Letters

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“…The results are shown in Table 1, which also gives the important propulsion and vehicle parameters. In obtaining these results we utilized the virial theorem (Litchford, Bitteker, and Jones, 2001) in calculating the magnet mass using Beryllium-Copper composite for the magnet material and assumed an advanced radiator design and material that allow the rejection of 64 MW per metric ton. Although the ion temperature was assumed to be 10 keV, they leave the GDM thruster at about 50 keV energy due to the presence of the electrostatic potential whose energy is superimposed on their escape (from the mirror) energy.…”

Section: Application To Mars Missionmentioning

confidence: 99%

The Gasdynamic Mirror Fusion Propulsion System — Revisited

Kammash¹,

Tang²

2005

AIP Conference Proceedings

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Many of the previous studies assessing the capability of the gasdynamic mirror (GDM) fusion propulsion system employed analyses that ignored the "ambipolar" potential. This electrostatic potential arises as a result of the rapid escape of the electrons due to their small mass. As they escape, they leave behind an excess positive charge which manifests itself in an electric field that slows down the electrons while speeding up the ions until their respective axial diffusions are equalized. The indirect effect on the ions is that their confinement time is reduced relative to that of zero potential, and hence the plasma length must be increased to accommodate that change. But as they emerge from the thruster mirror -which serves as a magnetic nozzle -the ions acquire an added energy equal to that of the potential energy, and that in turn manifests itself in increased specific impulse and thrust. We assess the propulsive performance of the GDM thruster, based on the more rigorous theory, by applying it to a round trip Mars mission employing a continuous burn acceleration/deceleration type of trajectory. We find that the length of the device and travel time decrease with increasing plasma density, while the total vehicle mass reaches a minimum at a plasma density of 3 × 10 16 cm -3 . At such a density, and an initial DT ion temperature of 10 keV, a travel time of 60 days is found to be achievable at GDM propulsion parameters of about 200,000 seconds of specific impulse and approximately 47 kN of thrust.

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Prospects for nuclear electric propulsion using closed cycle magnetohydrodynamic energy conversion

Cited by 26 publications

References 10 publications

Study on Specific Mass of Nuclear Electric Propulsion System with Closed Cycle MHD Generator

Study on Specific Mass of Nuclear Electric Propulsion System with Closed Cycle MHD Generator

Suppression of ionization instability in a magnetohydrodynamic plasma by coupling with a radio-frequency electromagnetic field

The Gasdynamic Mirror Fusion Propulsion System — Revisited

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