Volume 2, 2011Progress in Propulsion Physics
|Page(s)||629 - 638|
|Published online||01 October 2012|
Electric propulsion systems for small satellites: the low earth orbit mission perseus
Institut für Raumfahrtsysteme (IRS) Universität Stuttgart Pfaffenwaldring 31, Stuttgart 70569, Germany
2 Department of Advanced Energy University of Tokyo Kashiwa-no-ha 5-1-5, Kashiwa 277-8561, Japan
The Institute of Space Systems, Universität Stuttgart, launched a “Small a Satellite Program” in 2002. The first two of the four planed small satellites, Flying Laptop and PERSEUS, are both Low Earth Orbit (LEO) missions. The third mission Cermit is a reentry satellite and the last of the small satellites − Lunar Mission BW1 − is a mission to the Moon. For this purpose, different propulsion systems are mandatory. The propulsion system for Lunar Mission BW1 will consist of two different types of thruster systems: a cluster of pulsed magnetoplasmadynamic (MPD) thrusters (SIMP-LEX) using solid polytetrafluoroethylene (PTFE) as propellant and a thermal arcjet thruster (TALOS) using gaseous ammonia as propellant. Both thruster systems are currently under development at IRS. They are planned to be tested on board the small satellite mission PERSEUS, one of the precursor missions of Lunar Mission BW1. The thruster systems have been investigated intensely in the past and, furthermore, optimization of the thrusters with respect to the mission requirements of Lunar Mission BW1 has been started. The test procedures for the technology demonstration on the PERSEUS satellite are under development at present.
© Owned by the authors, published by EDP Sciences, 2011