Numerical Simulation of a Plasma Plume Exhaust from an Electrothermal Plasma Thruster

2005 ◽  
Vol 21 (2) ◽  
pp. 378-382 ◽  
Author(s):  
Leonid A. Bazyma ◽  
Vasyl M. Rashkovan
Keyword(s):  
Numerical Simulation ◽  
Plasma Plume ◽  
Electrothermal Plasma ◽  
Plasma Thruster

Numerical Simulation of Chemical Reactions on Rarefied Plasma Plume by DSMC Method

2021 ◽  
Vol 49 (3) ◽  
pp. 1214-1226
Author(s):  
Yongyuan Su ◽  
Jie Li ◽  
Haoyu Wang ◽  
Ao Xu
Keyword(s):  
Numerical Simulation ◽  
Chemical Reactions ◽  
Plasma Plume ◽  
Dsmc Method

scholarly journals Method of the electron distribution function calculation in a problem of the kinetic rarefied plasma plume modeling

2021 ◽  
Vol 2056 (1) ◽  
pp. 012022
Author(s):  
A M Bishaev ◽  
M V Abgaryan
Keyword(s):  
Plasma Plume ◽  
Electron Distribution Function ◽  
Distribution Functions ◽  
Plasma Component ◽  
Stationary Plasma Thruster ◽  
Stationary Plasma ◽  
Plasma Thruster ◽  
Plume Modeling ◽  
Function Calculation ◽  
Stated Problem

Abstract A problem related to the rarefied plasma plume of the stationary plasma thruster (SPT) is considered in the paper. The consideration is conducted fully in terms of kinetics, namely, distribution functions are introduced to describe motion of every plasma component. The system of kinetics equations for the distribution functions should be solved in combination with the Maxwell’s equations. The paper discusses methods for solving the stated problem.

Time-resolved investigation of the asymmetric plasma plume in a pulsed plasma thruster

2020 ◽  
Vol 53 (47) ◽  
pp. 475201
Author(s):  
Zhe Zhang ◽  
Zun Zhang ◽  
William Yeong Liang Ling ◽  
Xing Han ◽  
Jiangning Zhou ◽  
...  
Keyword(s):  
Plasma Plume ◽  
Pulsed Plasma ◽  
Time Resolved ◽  
Pulsed Plasma Thruster ◽  
Plasma Thruster

scholarly journals Experimental Characterization of the Capacitively Coupled RF-Plasma Thruster

2021 ◽  
Vol 11 (15) ◽  
pp. 6799
Author(s):  
Pavel Smirnov ◽  
Ruslan Kozakov ◽  
Jochen Schein
Keyword(s):  
Plasma Plume ◽  
Potential Drop ◽  
Rf Discharge ◽  
Rf Plasma ◽  
Capacitively Coupled ◽  
Plasma Generation ◽  
Magnetic Nozzle ◽  
Plasma Thruster ◽  
Nozzle Configuration ◽  
Emissive Probes

A novel design of a neutralizer-free plasma thruster is proposed. This setup features a capacitively coupled RF discharge for plasma generation combined with a magnetic nozzle configuration for acceleration. Characteristics of the plasma plume and ions flux are investigated with the help of emissive probes and retarding potential analyzers (RPA). Essential parameters of the thruster like ions energy, ions flux, utilization efficiencies, and thrust are estimated. The investigated system produces a beam of ions accelerated to an energy of 10 eV when operated at power levels of ~20 W and a mass flow of 1.2 mg/s. The ion energy coincides with the potential drop in the plasma plume indicating that the acceleration takes place due the formation of an ambipolar electric field in the expanding plasma. The design is compared to the data available of other similar thrusters.

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