Propellant Utilization Efficiency in a Pulsed Plasma Thruster-Reference-Cited by-同舟云学术

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Propellant Utilization Efficiency in a Pulsed Plasma Thruster

Published:2013-11 Issue:6 Volume:29 Page:1478-1487
ISSN:0748-4658
Container-title:Journal of Propulsion and Power
language:en
Short-container-title:Journal of Propulsion and Power

Author:

Schönherr Tony¹,Komurasaki Kimiya²,Herdrich Georg³

Affiliation:

1. Department of Aeronautics and Astronautics, University of Tokyo, Bunkyo, Tokyo 113-8656, Japan

2. Department of Advanced Energy, University of Tokyo, Kashiwa, Chiba 277-8561, Japan

3. Institute for Space Systems, University of Stuttgart, 70569 Stuttgart, Baden–Württemberg, Germany

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.B34789

Reference18 articles.

1. Pulsed Plasma Thruster

2. Analysis of effective parameters on ablative PPT performance

3. Electric propulsion systems for small satellites: the low earth orbit mission perseus

4. Thrust efficiency optimization of the pulsed plasma thruster SIMP-LEX

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1. Influences of initial voltage and electrode size on propellant surface evolution in a coaxial pulsed plasma thruster;Acta Astronautica;2024-09

2. Modeling and Simulation on the Ionization Process of the Coaxial Pulsed Plasma Thruster;2024 IEEE International Conference on Plasma Science (ICOPS);2024-06-16

3. Analysis of composition and dynamics of the plasma plume emitted by a 1 J pulsed plasma thruster fed with polytetrafluoroethylene and determination of thruster efficiency components;Physics of Plasmas;2024-05-01

4. Pulsed plasma thruster exhaust reconstruction;Plasma Sources Science and Technology;2024-04-01

5. Performance of pulsed plasma thruster at low discharge energy;Plasma Science and Technology;2023-11-16

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