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An Interstellar – Heliopause mission using a combination of solar/radioisotope electric propulsion
(2011)
There is common agreement within the scientific community that in order to understand our local galactic environment it will be necessary to send a spacecraft into the region beyond the solar wind termination shock. Considering distances of 200 AU for a new mission, one needs a spacecraft travelling at a speed of close to 10 AU/yr in order to keep the mission duration in the range of less than 25 yrs, a transfer time postulated by ESA.Two propulsion options for the mission have been proposed and discussed so far: the solar sail propulsion and the ballistic/radioisotope electric propulsion. As a further alternative, we here investigate a combination of solar-electric propulsion and radioisotope-electric propulsion. The solar-electric propulsion stage consists of six 22 cm diameter “RIT-22”ion thrusters working with a high specific impulse of 7377 s corresponding to a positive grid voltage of 5 kV. Solar power of 53 kW BOM is provided by a light-weight solar array. The REP-stage consists of four space-proven 10 cm diameter “RIT-10” ion thrusters that will be operating one after the other for 9 yrs in total. Four advanced radioisotope generators provide 648 W at BOM. The scientific instrument package is oriented at earlier studies. For its mass and electric power requirement 35 kg and 35 W are assessed, respectively. Optimized trajectory calculations, treated in a separate contribution, are based on our “InTrance” method.The program yields a burn out of the REP stage in a distance of 79.6 AU for a usage of 154 kg of Xe propellant. With a C3 = 45,1 (km/s)2 a heliocentric probe velocity of 10 AU/yr is reached at this distance, provided a close Jupiter gravity assist adds a velocity increment of 2.7 AU/yr. A transfer time of 23.8 yrs results for this scenario requiring about 450 kg Xe for the SEP stage, jettisoned at 3 AU. We interpret the SEP/REP propulsion as a competing alternative to solar sail and ballistic/REP propulsion. Omiting a Jupiter fly-by even allows more launch flexibility, leaving the mission duration in the range of the ESA specification.
Inhaltsverzeichnis: 4 Grußwort des Dekans [Prof. Dr.-Ing. Jürgen Kettern] 4 Grußwort des Sektionsleiters "Bau" des alfha.net [Dipl.-Ing. Walter Kleiker] 5 Referenten 10 Referate 10 Die Statik bleibt dynamisch ... : Beispiele der Schwingungsanfälligkeit von Brücken, Türmen und erdbebengefährdeten Gebäuden / Dipl.-Ing. Sebastian Gokus 12 Bau einer Biogasanlage / Dipl.-Ing. Michaela Schneider 16 Die neue Landmarke an der A4 / Dipl.-Ing. Franz-Josef Türck-Hövener 18 Technical Due Diligence Real Estate : Technische Immobilienbewertung zur Vorbereitung einer Immobilientransaktion - Eine Teilanalyse von Chancen und Risiken im Due Diligence Prozess / Dipl.-Ing. Architektin Ebru Baykal M.Eng. 20 Die Deutsche Botschaft Kabul wird saniert / Dipl.-Ing. Stefanie Milde 24 Abfluss- und Strukturverbesserung am Niederrhein : Ein hydraulischer Ansatz zur Vereinbarkeit von Hochwasserschutz und Strukturverbesserung / Dr.-Ing. Gesa Kutschera 26 Um- und Ausbau des Autobahnkreuzes Aachen / Dipl.-Ing. Dirk Gobbelé 30 Textilbewehrter Beton in Großprojekten am Beispiel einer Fußgängerbrücke / Dipl.-Ing. Andre Nacken 32 Kalkulation in der Bauindustrie / Dipl.-Ing. Alexander Spix 34 Phoenix-See Dortmund : Standort für die Zukunft / Dipl,-Ing. Stephan Bendel ; Dipl.-Ing. Sebastian Nyßen 38 alfha.net - Ein Verein stellt sich vor 39 Impressum
Air-sand heat exchanger
(2011)