Computer Science – Performance
Scientific paper
Jan 2002
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2002iaf..confe.801b&link_type=abstract
IAF abstracts, 34th COSPAR Scientific Assembly, The Second World Space Congress, held 10-19 October, 2002 in Houston, TX, USA.,
Computer Science
Performance
Scientific paper
R &D work on ion thrusters using radio frequency propellant ionisation has been done at Giessen University since 1962. Engines with ionizer diameters from 4 cm to 35 cm have been designed, built, and tested. Plasma and beam diagnostics have been done and several application studies were carried out. The present work at the 1. Institute of Physics is mainly focussed on two topics: First: The RF-plasma is being modelled in detail in order to establish scaling laws which will allow to scale the existing hardware and save D &Q work. Determination of basic plasma effects shall allow to find the optimum geometry and working parameters (e.g. the discharge vessel length, the best rf-frequency and the necessary discharge pressure). Then, reliable thrust, power, flow rate and efficiency data of different sized RIT-systems can be predicted. Second: The large Giessen test facility "P100,000" (with 30 m3 of chamber volume) has been completely refurbished, to allow the operation of Astriums new 22 cm diam thruster RIT-XT: The oil diffusion pumps were replaced by several cryopumps and two additional turbomolecular pumps. The conical beam target (stainless steel) has been replaced by inclined carbon collector strips. A new beam scanning system has been installed, which can be moved during operation in y- and z- direction. The scanner consists of 160 specially designed Faraday cups. Other diagnostic elements like calorimetric systems, small mass spectrometers etc. can be installed on the scanner, too. The development in the industry did start at Astrium (former MBB) in 1970 with the investigation of the 10 cm discharge chamber diameter laboratory thruster (RIT 10) manufactured in Giessen, using Mercury as the propellant. A first vibration test and a 1000-h lifetime test was performed and did show that the thruster can be used in space. The first 10 years of industrial development were filled with development of electronics, propellant feed system, thruster design and additional lifetime tests. First applications were planned for North- South-Stationkeeping on communication satellites, which did not realise. A first test in space was performed on the European Retrievable Carrier EURECA in 1992 using Xenon as the propellant which did demonstrate that the thruster can produce 10 mN of thrust and does not disturb the satellite operation. In parallel thrusters with 26 and 35 cm discharge chamber diameter have been manufactured and tested up to a thrust level of 200 mN for an application to interplanetary missions. For a first application to North-South-Stationkeeping of a geostationary satellite the thrust level of the RIT 10 has been increased to 15 mN. 2 RIT - thrusters are installed on the Artemis satellite next to 2 EIT thrusters, produced by Matra-Marconi-Space (now Astrium GB), which are using the "Kaufmann" ionisation principle. The satellite has been launched in July 2001 and is now, after a degraded launch performance of Ariane V, on the way to its geostationary position, propelled by ion thrusters. In parallel to this activity Astrium has started the development of the 22 cm discharge chamber diameter thruster RIT -XT, which shall be used for future application to commercial satellites and to interplanetary missions. Thrust levels up to 200 mN at a specific impulse up to 4500 s can be achieved. Competitive prices can be achieved if more than 10 systems can be produced per year.
Bassner Helmut
Killinger Rainer
Kukies Ralf
Mueller Jennifer
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