Computational modeling of expanded plasma plumes in vacuum and in a tank
Name
47095319-MIT.pdf
Description
Full printable version
Size
30.68 MB
Format
Adobe PDF
Checksum (MD5)
a3066d5deecbe51ffb3bc4e0528e37fb
Author(s)
Asare, Bernard K. (Bernard Kwaku), 1972-
Advisor(s)
Manuel Martinez-Sanchez.
Date Issued
1999
Publisher
Massachusetts Institute of Technology
Abstract
Electric propulsion devices have shown to offer substantial fuel savings for various space missions. Hall thrusters, specifically, have shown great promise over the years due to their near optimum specific impulse for a number of space missions. The Hall thruster, however, releases a partially ionized plasma plume which contaminates any surface it comes into contact with. Backflow contamination can lead to sputtering and effluent deposition on critical spacecraft components. A computational method for studying these interactions was developed by David Oh in 1997. He developed a Particle-in-Cell and Direct Simulation Monte Carlo (PIC-DSMC) algorithm to model the expansion of a plasma plume from a Hall thruster into a vacuum. In his work he implemented a plasma-surface interaction model which determined erosion rates on surfaces made of quartz, silicon and silver but he did not track the surface material removed. In this work Oh's model is expanded to include the removal and tracking of material from generic spacecraft surfaces and the walls of a vacuum tank. Sputtering yields adopted in this model are based on sputtering theory developed by Matsunami and Yamamura. Since the plasma can have a negative impact on spacecraft subcomponents, a method for protecting the spacecraft (in the form of a protective shield) is proposed, studied, and recommendations are discussed.
Description
Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1999.
Includes bibliographical references (leaves 143-149).
Subjects
Aeronautics and Astronautics.
MIT Department
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics
Terms of Use
M.I.T. theses are protected by
copyright. They may be viewed from this source for any purpose, but
reproduction or distribution in any format is prohibited without written
permission. See provided URL for inquiries about permission.
copyright. They may be viewed from this source for any purpose, but
reproduction or distribution in any format is prohibited without written
permission. See provided URL for inquiries about permission.
Persistent DSpace Link
