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Erosion and Performance Scaling of Electrodeless Plasma Thrusters with a Magnetic Nozzle.

紀錄類型:	書目-電子資源 : Monograph/item
正題名/作者:	Erosion and Performance Scaling of Electrodeless Plasma Thrusters with a Magnetic Nozzle./
作者:	Ha, Sungyoung.
面頁冊數:	1 online resource (74 pages)
附註:	Source: Masters Abstracts International, Volume: 83-02.
Contained By:	Masters Abstracts International83-02.
標題:	Aerospace engineering. -
電子資源:	http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=28545732click for full text (PQDT)
ISBN:	9798535500539

Erosion and Performance Scaling of Electrodeless Plasma Thrusters with a Magnetic Nozzle.
Ha, Sungyoung.

Erosion and Performance Scaling of Electrodeless Plasma Thrusters with a Magnetic Nozzle. - 1 online resource (74 pages)

Source: Masters Abstracts International, Volume: 83-02.

Thesis (Master's)--University of Washington, 2021.

Includes bibliographical references

The scaling of erosion and performance characteristics of electrodeless plasma thrusters with magnetic nozzles is investigated analytically and numerically. A quasi 1-D, two species model was used in conjunction with sheath and sputtering models to develop a numerical scheme for erosion rates and thruster performance. Analytical scaling laws were derived for thrust efficiency and erosion rates and analyzed through the numerical model. Wall impulse, which is derived as the total impulse obtained per unit thickness of wall material eroded, was analyzed as an objective metric for lifetime characteristics. Scaling laws strongly depended on the dominant diffusion mechanism, and the inclusion of anomalous transport introduced unique trade-offs between thrust efficiency and wall impulse. Generalized asymptotic scaling laws for thrust efficiency and wall impulse were calculated for argon and xenon. Comparison with wall impulse of existing Hall thrusters suggest that the erosion rates in electrodeless plasma thrusters can be comparable to those of Hall thrusters and lifetime limitations cannot be ignored. In addition to the investigation of scaling laws, an EXB probe, or Wein filter, was designed and made as a diagnostic method for future research. The probe was tested on the SPACE Lab Alternative Propellant ECR eXperimental (APEX) thruster along with a Langmuir probe. The probe was able to collect velocity data as expected and was also able to distinguish doubly charged ions at high input powers. Direct correlation between the numerical model and measured data was not possible likely due to differences in geometry and energy injection methods.

Electronic reproduction.
Ann Arbor, Mich. :
ProQuest,
2023

Mode of access: World Wide Web

ISBN: 9798535500539Subjects--Topical Terms:

1002622
Aerospace engineering.
Subjects--Index Terms:

Electric PropulsionIndex Terms--Genre/Form:

542853
Electronic books.

Erosion and Performance Scaling of Electrodeless Plasma Thrusters with a Magnetic Nozzle.
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500 $a Source: Masters Abstracts International, Volume: 83-02.
500 $a Advisor: Little, Justin M.
502 $a Thesis (Master's)--University of Washington, 2021.
504 $a Includes bibliographical references
520 $a The scaling of erosion and performance characteristics of electrodeless plasma thrusters with magnetic nozzles is investigated analytically and numerically. A quasi 1-D, two species model was used in conjunction with sheath and sputtering models to develop a numerical scheme for erosion rates and thruster performance. Analytical scaling laws were derived for thrust efficiency and erosion rates and analyzed through the numerical model. Wall impulse, which is derived as the total impulse obtained per unit thickness of wall material eroded, was analyzed as an objective metric for lifetime characteristics. Scaling laws strongly depended on the dominant diffusion mechanism, and the inclusion of anomalous transport introduced unique trade-offs between thrust efficiency and wall impulse. Generalized asymptotic scaling laws for thrust efficiency and wall impulse were calculated for argon and xenon. Comparison with wall impulse of existing Hall thrusters suggest that the erosion rates in electrodeless plasma thrusters can be comparable to those of Hall thrusters and lifetime limitations cannot be ignored. In addition to the investigation of scaling laws, an EXB probe, or Wein filter, was designed and made as a diagnostic method for future research. The probe was tested on the SPACE Lab Alternative Propellant ECR eXperimental (APEX) thruster along with a Langmuir probe. The probe was able to collect velocity data as expected and was also able to distinguish doubly charged ions at high input powers. Direct correlation between the numerical model and measured data was not possible likely due to differences in geometry and energy injection methods.
533 $a Electronic reproduction. $b Ann Arbor, Mich. : $c ProQuest, $d 2023
538 $a Mode of access: World Wide Web
650 4 $a Aerospace engineering. $3 1002622
650 4 $a Plasma physics. $3 3175417
650 4 $a Engineering. $3 586835
650 4 $a Velocity. $3 3560495
650 4 $a Plasma. $3 877619
650 4 $a Electrodes. $3 629151
650 4 $a Trends. $3 3560051
650 4 $a Magnetic fields. $3 660770
650 4 $a Electric fields. $3 880423
650 4 $a Antennas. $3 3681648
650 4 $a Nozzles. $3 3693706
650 4 $a Approximation. $3 3560410
650 4 $a Heat. $3 573595
650 4 $a Physical properties. $3 3564184
650 4 $a Boundary conditions. $3 3560411
650 4 $a Geometry. $3 517251
650 4 $a Ordinary differential equations. $3 3563004
650 4 $a Efficiency. $3 753744
653 $a Electric Propulsion
653 $a EXB Probe
653 $a Helicon Thrusters
653 $a Magnetic Nozzle
653 $a Plasma Physics
653 $a Wein Filter
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710 2 $a University of Washington. $b Aeronautics and Astronautics. $3 2093881
773 0 $t Masters Abstracts International $g 83-02.
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