Highlights of Pulsed Plasma Development at IRS

Paper number

IAC-09.C4.P.17

Author

Mr. Tony Schönherr, The University of TOKYO, Graduate school, Japan

Coauthor

Dr. Georg Herdrich, Germany

Coauthor

Ms. Anuscheh Nawaz, University of Stuttgart, Germany

Coauthor

Mr. Matthias Lau, Institute of Space Systems, Universität Stuttgart, Germany

Year

2009

Abstract

The pulsed plasma thruster SIMP–LEX is developed at IRS in order to serve as main propulsion system for the planned lunar mission BW1. This satellite mission is an important step in the institute’s satellite research and development program including electric propulsion technology. During the last years and decades, a certain expertise was gathered on electric propulsion while building up thrusters of different working principles and energy levels. Following a development that lead to an engineering model of the PPT, several further investigations were conducted with the aim of an optimization of the thruster’s performance and lifetime expectancy. For that purpose a systematic campaign varying the geometrical and electrical properties of the thruster was performed and several performance variables measured. The parameters and their variations were chosen in respect of feasibility and results of further investigations on pulsed plasma thrusters. As for qualification, first investigations were conducted to verify the lifetime on component level as well as of the whole thruster system. 
In addition to the experimental investigations, the numerical model to simulate the behavior within the thruster’s oscillation circuit was adapted to allow for studies on the changed geometry. The results of the model were also compared with the information and data derived from the experimental investigations yielding a possibility of verifying the code. 
Consequent to the results of the studies conducted and with cooperative help of the RIAME MAI the design of the electrode geometry was changed to a 20 deg-flare angled configuration with a triangular shape. 
The electrode width was reduced to a value of 20 mm, while the gap between the electrodes was reduced to 21 mm. From the lifetime tests changes for the capacitors and the spark plug were determined. These modifications lead to a different configuration called ADD SIMP–LEX with significantly ameliorated performance characteristics and improved electrical properties, e.g., higher thrust efficiency, decreased circuit inductance and, correspondingly, higher exhaust velocity, compared to the previous model. 
The aim of current activities is related to the further improvement of the lifetime expectancy as well as the transformation of the engineering model to a model able to fly on the satellite. A summary of the activities and their results described above is presented within this paper as well as an outlook of the subsequent steps leading to a flight-ready thruster.

Abstract document

IAC-09.C4.P.17.pdf

Manuscript document

IAC-09.C4.P.17.pdf (🔒 authorized access only).

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