Plasma Structure of Miniature Ring-Cusp Ion Thruster Discharges
Author:
Affiliation:
1. Mechanical and Aerospace Engineering, University of California, Los Angeles, Los Angeles, California 90095
2. Propulsion and Materials Engineering Section, Jet Propulsion Laboratory, California Institute of Technology, Pasadena, California 91109
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Space and Planetary Science,Mechanical Engineering,Fuel Technology,Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.B34759
Reference16 articles.
1. Electric Propulsion and Controller Design for Drag-Free Spacecraft Operation
2. also AIAA Paper 2002-3835.
3. also AIAA Paper 2011-6083.
4. Ion source discharge performance and stability
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1. Revealing the plasma confinement behavior of an axial ring cusp hybrid discharge in a miniature ion thruster using PIC/MCC simulation;Plasma Sources Science and Technology;2023-08-01
2. Numerical investigation of plasma behavior in a micro DC ion thruster using the particle-in-cell/Monte Carlo collision (PIC/MCC) method;Journal of Physics D: Applied Physics;2021-08-20
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4. The effects of numerical acceleration techniques on PIC-MCC simulations of ion thrusters;AIP Advances;2020-04-01
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