Review of multimode space propulsion

Rovey, Joshua L.; Lyne, Christopher T.; Mundahl, Alex J.; Rasmont, Nicolas; Glascock, Matthew S.; Wainwright, Mitchell J.; Berg, Steven P.

doi:10.1016/j.paerosci.2020.100627

Cited by 63 publications

(31 citation statements)

References 58 publications

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“…These ions are accelerated out of channel by electric field at the channel exit and this motion of ions imparts a reaction force on the thruster in reverse direction. The cathode is also used to neutral the ions charge so it produce a stream of electron to neutral the ions [1][2][3][4][5][6][7][8][9][10].…”

Section: Description Of the Hall Thrustermentioning

confidence: 99%

“…The ratio of channel width and channel depth in these thruster is 2:1. The conducting channel wall is negatively biased and it is a part of magnetic circuit so it prevent electron to move in direction of wall and repel them to ionization region and reduce electron power losses [1][2][3][4][5][6][7][8][9][10].…”

Section: Thruster With Anode Layer (Tal)mentioning

confidence: 99%

“…This limitation of chemical thrusters opens up discussion of the use of electric thrusters, which provide much higher specific impulses. A high specific impulse allows the spacecraft to reach the same speed with lower propellant consumption than chemical ones or travel faster with the same propellant mass [1][2][3][4][5][6][7][8][9][10]. In addition, the use of a high specific impulse, electric thruster permits a significant reduction in propellant mass on spacecraft, which helps reduce launching cost, extending mission lifetime or increase the payload mass on the spacecraft [2].…”

Section: Introductionmentioning

confidence: 99%

“…On the thruster exterior, the ion beam is neutralized by electrons from the virtual cathode so that no charge builds up on the spacecraft's surface [2]. More details on Hall thruster operation and fundamentals can be found in [1][2][3][4][5][6][7][8][9][10][11][12][13].…”

Section: Introductionmentioning

confidence: 99%

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Numerical Investigations of Electromagnetic Oscillations and Turbulences in Hall Thrusters Using Two Fluid Approach

Singh¹,

Vidhani²,

Tyagi³

2022

Plasma Science and Technology

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The first part of the contributed chapter discuss the overview of electric propulsion technology and its requirement in different space missions. The technical terms specific impulse and thrust are explained with their relation to exhaust velocity. The shortcoming of the Hall thrusters and its erosion problems of the channel walls are also conveyed. The second part of the chapter discuss the various waves and electromagnetic instabilities propagating in a Hall thruster magnetized plasma. The dispersion relation for the azimuthal growing waves is derived analytically with the help of magnetohydrodynamics theory. It is depicted that the growth rate of the instability increases with magnetic field, electron drift velocity and collisional frequency, whereas it is decreases with the initial drift of the ions.

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Section: Description Of the Hall Thrustermentioning

confidence: 99%

Section: Thruster With Anode Layer (Tal)mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Numerical Investigations of Electromagnetic Oscillations and Turbulences in Hall Thrusters Using Two Fluid Approach

Singh¹,

Vidhani²,

Tyagi³

2022

Plasma Science and Technology

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“…They are highlighted in the ESA CleanSpace initiative [78]. One possible reason for this is because arcjets are particularly suited to multi-mode propulsion systems in which more than one propellant is shared amongst the propellant feed system [87]. Enabling the arcjet to potentially utilise in-situ space resources or waste products from chemical rockets even when depleted of propellant.…”

Section: Arcjetmentioning

confidence: 99%

Electric Propulsion Methods for Small Satellites: A Review

2021

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Over 2500 active satellites are in orbit as of October 2020, with an increase of ~1000 smallsats in the past two years. Since 2012, over 1700 smallsats have been launched into orbit. It is projected that by 2025, there will be 1000 smallsats launched per year. Currently, these satellites do not have sufficient delta v capabilities for missions beyond Earth orbit. They are confined to their pre-selected orbit and in most cases, they cannot avoid collisions. Propulsion systems on smallsats provide orbital manoeuvring, station keeping, collision avoidance and safer de-orbit strategies. In return, this enables longer duration, higher functionality missions beyond Earth orbit. This article has reviewed electrostatic, electrothermal and electromagnetic propulsion methods based on state of the art research and the current knowledge base. Performance metrics by which these space propulsion systems can be evaluated are presented. The article outlines some of the existing limitations and shortcomings of current electric propulsion thruster systems and technologies. Moreover, the discussion contributes to the discourse by identifying potential research avenues to improve and advance electric propulsion systems for smallsats. The article has placed emphasis on space propulsion systems that are electric and enable interplanetary missions, while alternative approaches to propulsion have also received attention in the text, including light sails and nuclear electric propulsion amongst others.

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Microwave electrothermal thruster with surface wave plasma

Kiss'ovski,

Yordanov,

Marinov

et al. 2024

Contrib. Plasma Phys

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A new microwave electrothermal thruster (MET) with small dimensions (length of 25 mm and diameter of 6 mm), utilizing surface wave (SW) plasma at low average power consumption Pav ˜ 2 W, is made. It uses microwaves at a frequency of 2.45 GHz for plasma generation within a dielectric chamber enclosed in a metal shield. The SW is excited at the plasma‐dielectric interface by a coaxial launcher and a standing wave is created due to the wave reflection from the shield. The high‐density plasma produced in this resonant chamber heats up the argon gas, which expands through the nozzle in the axial direction. The temperature of the gas decreases from 1900 K at atmospheric pressure to 1200 K at 10 Torr ambient pressure. This small‐sized MET shows stable low‐pressure operation with a thrust of 4 mN and an efficiency of 8% and is suitable for nanosatellite orbit control.

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Review of multimode space propulsion

Cited by 63 publications

References 58 publications

Numerical Investigations of Electromagnetic Oscillations and Turbulences in Hall Thrusters Using Two Fluid Approach

Numerical Investigations of Electromagnetic Oscillations and Turbulences in Hall Thrusters Using Two Fluid Approach

Electric Propulsion Methods for Small Satellites: A Review

Microwave electrothermal thruster with surface wave plasma

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