Nature-Inspired Concepts for High-Power Electric Propulsion Systems

Shumeiko, Andrei I.

doi:10.1080/15361055.2023.2227504

Cited by 2 publications

(2 citation statements)

References 46 publications

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“…In addition, there are magnetic field strengths at which discharge breakdown is not possible at very low pressures when the electron mean free path, λ, is greater than the characteristic dimensions of the system, L system λ > L system [35]. Thus, it is necessary to add a coefficient to the fourth term in Equation ( 7)-which is b 1 B in Equation (10)-that reflects the increase in the magnetic field.…”

Section: Classical Diffusion Theorymentioning

confidence: 99%

“…This means that the spacecraft can be moved between orbital positions more quickly, consuming less power and propellant for a given maneuver in space compared to a conventional unidirectional PS. One of the most promising technologies for thrusters that are capable of generating propulsion in multiple directions is electrodeless plasma thrusters [4][5][6][7][8][9][10][11][12][13][14][15][16][17][18][19][20]. Electrodeless plasma thrusters are based on sources that typically consist of a gas discharge chamber, a magnetic system, and an antenna with a high-frequency (HF), radiofrequency (RF), or microwave (mw) power supply.…”

Section: Introductionmentioning

confidence: 99%

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Starting Modes of Bi-Directional Plasma Thruster Utilizing Krypton

Shumeiko,

Telekh,

Ryzhkov

2023

Symmetry

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Multidirectional plasma thrusters are of particular interest for dynamic space missions due to the adjustability of their integral characteristics. One type of multidirectional plasma thrusters is -directional, consisting of a symmetric electromagnetic system surrounding the gas discharge chamber, capable of generating a propulsion minimum in two directions. The experimental results of this study of the starting modes of a multidirectional plasma thruster utilizing krypton as propellant are reported. The thruster is placed in a vacuum chamber. The magnetic field strength is adjusted in the range of 35 to 400 G in peaks. The current of 13.56 MHz frequency applied to the antenna is regulated in the range of 0 to 25 A. The diameter of the orifices is varied in the range of 3 to 10 mm. In contrast to the unidirectional electrodeless plasma thruster, the radiofrequency breakdown threshold of the multidirectional plasma thruster decreases with increasing static magnetic field due to the symmetry of the magnetic system and the gas discharge chamber. The influence of the magnetic field on the radiofrequency breakdown threshold in the multidirectional plasma thruster is shown theoretically by the classical diffusion theory and ponderomotive effects, and discussed in the electron circulation hypothesis.

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Section: Classical Diffusion Theorymentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Starting Modes of Bi-Directional Plasma Thruster Utilizing Krypton

Shumeiko,

Telekh,

Ryzhkov

2023

Symmetry

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Numerical simulation of thermo-throttle for iodine flow rate control in multidirectional plasma thruster

Savelev,

Pashaev,

Shumeiko

2023

nuclscitechnolopenres

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Background: Recently, a new direction in the field of electric propulsion has emerged – the multidirectional plasma thrusters. These thrusters are capable of producing propulsive forces in multiple directions. The thrusters are proposed to be used for orbit maintenance and alterations, formation flights, and interplanetary flights of space artificial objects ranging in size from CubeSats to fusion-powered interplanetary spacecraft. In this paper, the results of numerical simulation of the iodine propellant supply system for the multidirectional plasma thruster are presented. Methods: The geometry and temperature parameters of propellant supply system various elements are varied to determine the stable modes of iodine propellant ejection into the gas discharge chamber of the thruster. The temperatures of the thermo throttle and filter are found to ensure iodine mass flow rate in the range of 0.1 to 1.5 mg/s. The thermo throttle and filter temperatures are altered in the range of 65 to 200 °C and 65 to 100 °C, correspondingly. Results: The mass flow rate is critically dependent on the filter temperature and iodine saturated vapor pressure, as well as the filter and throttle geometries. The required values of iodine flow rate have been achieved by using the throttle with a diameter of 0.5 mm and a length of 60 mm and a filter with 56 holes, each hole diameter is 0.2 mm, and temperature from 90 C to 200 C. Conclusions: According to the data obtained, the iodine storage and supply system is preferably equipped with a thermos throttle, which provides precise control of the flow rate, as well as reduces sharp jumps of the flow rate when the temperature of the filter changes. Preferred filter geometry: 56 holes, each hole 0.2 mm in diameter.

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Nature-Inspired Concepts for High-Power Electric Propulsion Systems

Cited by 2 publications

References 46 publications

Starting Modes of Bi-Directional Plasma Thruster Utilizing Krypton

Starting Modes of Bi-Directional Plasma Thruster Utilizing Krypton

Numerical simulation of thermo-throttle for iodine flow rate control in multidirectional plasma thruster

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