State of the art of radio-frequency ion sources for space propulsion (abstract)a)

Groh, K.; Loeb, H.

doi:10.1063/1.1145025

Cited by 3 publications

(4 citation statements)

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“…Hall effect thrusters have shown a throttling capability of 75 -250 mN corresponding to a nominal specific impulse of 1500 s over a power range of 1.5 to 6 kW [17]. Gridded radio frequency ion thrusters such as the RIT series produce thrust ranging from 10 mN to 250 mN with increasing discharge chamber diameter [18]. The RIT 10 which operates at input powers comparable to the HDLT is a 10 mN thruster with a specific impulse of 3300 s. It should be noted that one of the key advantages of the HDLT is the capability to accelerate ions without the use of a system of grids.…”

Section: Resultsmentioning

confidence: 99%

Performance characterization of a helicon double layer thruster using direct thrust measurements

Pottinger

Lappas

Charles

et al. 2011

J. Phys. D: Appl. Phys.

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Abstract. The performance of a Helicon Double Layer Thruster (HDLT) has been characterised using a pendulum type thrust stand and retarding field energy analyser. Data recorded for a fixed propellant flow rate of 16 sccm of krypton and fixed magnetic field topology show that the thrust generated increases linearly with increasing radio frequency input power over a range of 250 W to 650 W. Over the power range investigated thrust levels of approximately 1 to 2.8 mN were achieved. A maximum effective specific impulse of 280 s was determined using the thrust data. Ion energy distribution functions indicate that increasing power corresponds to improved plasma generation processes as general trends show increasing plasma and beam currents with increasing power.

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Section: Resultsmentioning

confidence: 99%

Performance characterization of a helicon double layer thruster using direct thrust measurements

Pottinger

Lappas

Charles

et al. 2011

J. Phys. D: Appl. Phys.

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“…Many detailed articles about the physics, the limitations and applications of ion engines have been published, see e.g. references [3,5,6,58,59,60,61]. Here, we only propose an overview of the working principles with emphasis on ion production methods and thrust generation.…”

Section: Architecture and Operation Principlementioning

confidence: 99%

“…Ionization can be achieved by means of waves as well. An external inductive coil wound around the thruster body can inductively couple a RF wave to the plasma [60,61,62,63,64,65,66]. The energy is then deposited close to the dielectric walls in a narrow region of the size of the electron skin depth where an evanescent electric field exists.…”

Section: Architecture and Operation Principlementioning

confidence: 99%

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

Mazouffre

2016

Plasma Sources Sci. Technol.

420

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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“…The gridded ion engine is an ion accelerator in which the thrust density is achieved through electrostatic interactions [5][6][7][8][9]. The propellant ionization and ion acceleration processes are physically separated in this device, which permits a fine tuning of thrust and exhaust velocity.…”

Section: Introductionmentioning

confidence: 99%

A new ion–ion plasma thruster with an annular geometry

Mazouffre

Renaud

2017

Eur. Phys. J. D

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The concept of ion-ion plasma thruster relies on a magnetic filter to create an electron-free plasma in the ion current extraction region. However, experiments and computer simulations show a transverse magnetic field makes the discharge asymmetrical due to electron drift and instabilities in the region of strong magnetic field. The drift drives a large electron flux to the walls, therefore increasing losses, and reduces the electron confinement by creating an escape path throughout the magnetic filter, which is detrimental for the thruster performances. We present a new architecture for an ion-ion plasma thruster that allows to cancel the asymmetry of the plasma by closing in the electron drift on itself. The concept is termed AIPE, an acronym for Annular Ion-ion Plasma Engine. A prototype was developed and tested with noble gases and SF6. Outcomes of experiments dedicated to the examination of the AIPE discharge and beam by means of Langmuir probe, E×B probe and laser photodetachment are given and discussed. It is shown that the discharge is symmetrical and homogeneous. In addition, positive and negative ions can be extracted and accelerated through the grid assembly.

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State of the art of radio-frequency ion sources for space propulsion (abstract)a)

Cited by 3 publications

References 0 publications

Performance characterization of a helicon double layer thruster using direct thrust measurements

Performance characterization of a helicon double layer thruster using direct thrust measurements

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

A new ion–ion plasma thruster with an annular geometry

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