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

Abstract

The Institute of Space Systems, Universit at Stuttgart, launched a ¤Small Satellite Program¥ in 2002. The ¦rst 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, di¨erent 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 polytetra §uoroethy-lene (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.

Review of Pulsed Plasma Thruster Development at IRS

“…Scheduled to be placed in a low Earth orbit (LEO), the satellite is intended to have a mass of less than 150 kg comprising one arcjet thruster and one pulsed plasma thruster (PPT). After the in-orbit validation of the performance characteristics and the operational behavior, the subsequently refined thrusters will be applied to the Lunar Mission BW1 2) . As a first step of the development of the PPT, an engineering model was set up and first operational tests and scientific investigations were launched 2,3) .…”

“…After the in-orbit validation of the performance characteristics and the operational behavior, the subsequently refined thrusters will be applied to the Lunar Mission BW1 2) . As a first step of the development of the PPT, an engineering model was set up and first operational tests and scientific investigations were launched 2,3) . Concurrently, the modeling of the thruster was envisaged in order to compare with experimental results as well as to obtain a better understanding of the related physical theories.…”