Plasma flow processes within magnetic nozzle configurations

York, Thomas M.; Mikellides, Pavlos G.; Jacoby, B. A.

doi:10.2514/6.1989-2711

Cited by 5 publications

(5 citation statements)

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“…York's 12 and Hoopers's 13 model considers a single-fluid MHD flow for given magnetic field. The condition for detachment in Hooper's study is given by the scaling parameter G < 2,750, defined as G = (eB z r p (z 0 )) 2 / (m e m i (2u(z 0 )) 2 ).…”

Section: Previous Plasma Detachment Studiesmentioning

confidence: 99%

“…The calculation of B p should be iterated with the calculation of plasma velocity and density. Figure 8 demonstrates the plasma current density due to the curvature of the magnetic field calculated by formula (12) and the magnetic field calculated by equation (13). In the plasma exhaust, the plasma magnetic field lines approach the direction of the z-axis.…”

Section: American Institute Of Aeronautics and Astronauticsmentioning

confidence: 99%

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Simulation of plasma detachment in VASIMR

Ilin¹,

Chan²,

Squire³

et al. 2002

40th AIAA Aerospace Sciences Meeting &Amp; Exhibit

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Section: Previous Plasma Detachment Studiesmentioning

confidence: 99%

Section: American Institute Of Aeronautics and Astronauticsmentioning

confidence: 99%

Simulation of plasma detachment in VASIMR

Ilin¹,

Chan²,

Squire³

et al. 2002

40th AIAA Aerospace Sciences Meeting &Amp; Exhibit

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“…In their basic design, MNs consist of an axisymmetric, convergent-divergent magnetic field B that guides the expansion of a hot plasma to form a supersonic jet. Their operation principles are now well understood [22][23][24][25][26] and have been observed experimentally 18,19,[27][28][29][30][31][32][33] : in the MN, ions gain axial kinetic energy at the expense of electron internal energy thanks to the mediation of the selfconsistent electric field. Additional plasma acceleration a) Electronic mail: mario.merino@uc3m.es; http://ep2.uc3m.es mechanisms exist in some devices like the VASIMR which rely on ion internal energy rather than electron internal energy.…”

Section: Introductionmentioning

confidence: 99%

Contactless steering of a plasma jet with a 3D magnetic nozzle

Merino

Ahedo

2017

Plasma Sources Sci. Technol.

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A 3D, steerable magnetic nozzle is presented that enables contactless thrust vector control of a plasma jet without any moving parts. The concept represents a substantial simplification over current plasma thruster gimbaled platforms, and requires only a small modification in thrusters that already have a magnetic nozzle. The characteristics of the plasma expansion in the 3D magnetic field and the deflection performance of the device are characterized with a fully-magnetized plasma model, suggesting that thrust deflections of 5-10 deg are readily achievable.

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“…The three plasma thruster concepts previously described, along with the applied-field MPD engine, employ as acceleration stage an expanding magnetic field that forms a divergent magnetic nozzle (MN) [10,180,181,182]. The purpose of a MN is to transform the internal energy of the plasma into axially directed ion kinetic energy.…”

Section: Principle Of a Magnetic Nozzlementioning

confidence: 99%

Electric propulsion for satellites and spacecraft: established technologies and novel approaches

Mazouffre

2016

Plasma Sources Sci. Technol.

433

263

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This contribution presents a short review of electric propulsion technologies for satellites and spacecraft. Electric thrusters, also termed ion or plasma thrusters, deliver a low thrust level compared to their chemical counterparts, but they offer significant advantages for in-space propulsion as energy is uncoupled to the propellant, therefore allowing for large energy densities. Although the development of EP goes back to the 1960's, the technology potential has just begun to be fully exploited because of the increase in the available power aboard spacecrafts, as demonstrated by the very recent appearance of all-electric communication satellites. This article first describes the fundamentals of EP: momentum conservation and the ideal rocket equation, specific impulse and thrust, figures of merit and a comparison with chemical propulsion. Subsequently, the influence of the power source type and characteristics on the mission profile is discussed. Plasma thrusters are classically grouped into three categories according to the thrust generation process: electrothermal, electrostatic and electromagnetic devices. The three groups, along with the associated plasma discharge and energy transfer mechanisms, are presented via a discussion of long-standing technologies like arcjet thrusters, MPD thrusters, pulsed plasma thrusters, ion engines as well as Hall thrusters and variants. More advanced concepts and new approaches for performance improvement are discussed afterwards: magnetic shielding and wall-less configurations, negative ion thrusters, and plasma acceleration with a magnetic nozzle. Finally, various alternative propellant options are analyzed and possible research paths for the near future are examined.

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Plasma flow processes within magnetic nozzle configurations

Cited by 5 publications

References 0 publications

Simulation of plasma detachment in VASIMR

Simulation of plasma detachment in VASIMR

Contactless steering of a plasma jet with a 3D magnetic nozzle

Electric propulsion for satellites and spacecraft: established technologies and novel approaches

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