The research objective for this project was to investigate and resolve technical issues associated with electric propulsion thrusters, specifically performance and spacecraft integration issues. The thrusters examined include magneto-plasma-dynamic (MPD) thrusters, arcjets, Hall thrusters, and pulsed plasma thrusters. The specific tasks were to identify methods to significantly increase MPD efficiencies, characterize and test laboratory arcjets in support of flight experiments, demonstrate significant gains in impulse to wet mass ratios for Hall thrusters, and develop and test advanced PPT design concepts. Results are summarized and more detail is provided in 34 referenced papers and journal articles.


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    Plasma separator ion thruster development

    FREE, B. / MICKELSEN, W. | AIAA | 1966


    Development of Helicon Plasma Thruster Model

    Kuzenov, Victor / Seleznev, Roman / Ryzhkov, Sergey | AIAA | 2017



    Micro Pulsed Plasma Thruster Technology Development

    Simon, Daniel / Land, H Bruce | AIAA | 2004


    Pulsed Plasma Thruster

    Burton, R. L. / Turchi, P. J. | British Library Conference Proceedings | 1998