Increased Thrust-to-Power Ratio of a Stepped-Diameter Helicon Plasma Thruster with Krypton Propellant
Author:
Affiliation:
1. Tohoku University, Sendai 980-8579, Japan
2. Yokohama National University, Yokohama 240-8501, Japan
Funder
Japan Society for the Promotion of Science
Japan Aerospace Exploration Agency
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Space and Planetary Science,Mechanical Engineering,Fuel Technology,Aerospace Engineering
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