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Thermal Analysis of Propellant Injector for a High Performance Electrodeless Plasma Thruster
2014 (English)Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
Abstract [en]

The High Performance Electric Propulsion Project of the Swedish space company OHB Sweden is focussed on combining the advantages of an electrodeless plasma thruster with the energetic monopropellant LMP-103S, developed by the Swedish Defense Research Agency. A satellite could use this type of electric propulsion device operating with a chemical propellant for apogee raising during its transfer to geostationary orbit. Sharing one propellant tank with two propulsion systems offers a reduction in mass and cost compared to conventional individual propulsion systems. The work presented is focussed on thermal analysis of the propellant injector. Water was used as a simulant for LMP-103S in order to determine the thermal behaviour of the injector at low mass flow rates. The problem of ice formation at the injector output was encountered and propositions for solutions were found. In addition, fluid dynamic simulations of a xenon flow through different pipe geometries were conducted with the software package OpenFOAM as a first step of predicting the thruster's performance when operated with noble gases.

Place, publisher, year, edition, pages
2014. , 49 p.
Keyword [en]
Keyword [sv]
URN: urn:nbn:se:ltu:diva-56808Local ID: d8b98286-e8ad-4ea2-b329-f75b7dc2f4e6OAI: diva2:1030195
Subject / course
Student thesis, at least 30 credits
Educational program
Space Engineering, master's level
Validerat; 20141028 (global_studentproject_submitter)Available from: 2016-10-04 Created: 2016-10-04Bibliographically approved

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