Computational modeling of a Hall thruster plasma plume in a vacuum tank
Author(s)Cheng, Shannon Yun-Ming, 1978-
Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics.
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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.
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).
DepartmentMassachusetts Institute of Technology. Dept. of Aeronautics and Astronautics.
Massachusetts Institute of Technology
Aeronautics and Astronautics.