Computational modeling of a Hall thruster plasma plume in a vacuum tank
Name
51272144-MIT.pdf
Description
Full printable version
Size
8.17 MB
Format
Adobe PDF
Checksum (MD5)
d8c745d8fdfcfc2b385e4a57a1c88501
Author(s)
Cheng, Shannon Yun-Ming, 1978-
Advisor(s)
Manuel Martinez-Sanchez.
Date Issued
2002
Publisher
Massachusetts Institute of Technology
Abstract
Hall thrusters have become a tempting alternative to traditional chemical propulsion systems due to the great mass savings they provide through high specific impulses. However, a major stumbling block to their widespread integration is uncertainty about the thruster plume's interaction with spacecraft components. While in-space data is difficult to collect, much experimental data from vacuum tank tests is readily available. Effectively taking advantage of this wealth requires understanding of the effects from imperfect ground test conditions. A previous plume model, Qasi3, has been upgraded to better simulate the vacuum tank environment primarily through improvements to the source model, the collision method, and the sputtering method. The code is now more accurate and provides insight into phenomena such as background pressure consequences. sputtering and sputtered material deposition.
Description
Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2002.
This electronic version was submitted by the student author. The certified thesis is available in the Institute Archives and Special Collections.
Includes bibliographical references (p. 169-171).
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.
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