State-of-the-art of radio-frequency ion thrusters

Groh, K.; Loeb, H.

doi:10.2514/6.1989-2381

Cited by 4 publications

(4 citation statements)

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“…Thrusters with electromagnetic acceleration are usually divided into two subclasses: magneto-plasma-dynamic thrusters with self-induced and applied magnetic field. Electrostatic thrusters include ion thrusters (IT) and colloid thrusters with various mechanisms of propellant ionization [5,6]. Pulsed Plasma Thrusters (PPT) are usually considered as a separate class [7] due to the pronounced specificity of operating processes.…”

Section: Types Of Low-power Electric Propulsion Systemsmentioning

confidence: 99%

Application of Low-Power Pulse Plasma Thrusters in Thrust Units of Small Spacecrafts

Bogatiy

Dyakonov

Elnikov

et al. 2021

Applied Mathematics and Computational Mechanics for Smart Applications

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The chapter considers the current state of work on flight models of pulsed plasma propulsion systems. It is shown that the primary application area for propulsion systems based on an ablative pulsed plasma thruster is the station-keeping of small spacecraft with the power of supply system of up to 100 W and with an active lifetime in a range from 1 to 10 years in low Earth orbits with altitudes in a range from 400 to 700 km. It is also shown that ablative pulsed plasma thrusters can be efficiently used to solve the problems of accurate attitude control and angular stabilization of spacecraft.

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Section: Types Of Low-power Electric Propulsion Systemsmentioning

confidence: 99%

Application of Low-Power Pulse Plasma Thrusters in Thrust Units of Small Spacecrafts

Bogatiy

Dyakonov

Elnikov

et al. 2021

Applied Mathematics and Computational Mechanics for Smart Applications

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show abstract

“…Figure 4 shows several performance data points as published in literature for several different small-scale electric propulsion thrusters. 15,[17][18][19][20][21] The NASA 8 cm thruster target operation on xenon is shown, as well as actual operating data for the Hayabusa "µ10" and RIT 10 thrusters also utilizing xenon as the propellant. As mentioned previously, investigation of the GEC source showed performance down to 250 W/A, with 1 A of extracted current.…”

Section: Performance Targets and Goalsmentioning

confidence: 99%

Low Power Planar Antenna Inductive Discharge Ion Source

Gillman¹,

Cummings²,

Foster³

2008

44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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“…[8][9][10][11][12][13] RF has been used as either a means for ion production in electrostatic thrusters, or a means to heat a fluid similarly to a microwave thruster operating a much lower frequency. RFCCD utilizes the RF component to contain as well as heat the ions produced by the glow discharge.…”

Section: Introductionmentioning

confidence: 99%