TY  - BOOK
A1  - Ley, Wilfried
T1  - Internationale Raumstation : Konfiguration, Betrieb und Nutzung ; Gemeinschaftsveranstaltung der FH Aachen, der DGLR und des DLR  / 11. Raumfahrt-Kolloquium an der Fachhochschule Aachen, 26. November 1998.  / Ley, Wilfried [Hrsg.]
Y1  - 1998
SN  - 3-932182-04-9
PB  - DGLR
CY  - Bonn
ER  - 
TY  - BOOK
A1  - Ley, Wilfried
T1  - Raumfahrtmissionen zur Erkundung des Sonnensystems : Gemeinschaftsveranstaltung der FH Aachen, der DGLR und des DLR / 10. Raumfahrt-Kolloquium an der Fachhochschule Aachen, 5. November 1997 / Ley, Wilfried [Hrsg.]
Y1  - 1997
SN  - 3-922010-99-7
PB  - DGLR
CY  - Bonn
ER  - 
TY  - BOOK
A1  - Ley, Wilfried
T1  - Trägersysteme : Gemeinschaftsveranstaltung der FH Aachen und der DGLR / 8. Raumfahrt-Kolloquium an der Fachhochschule Aachen, 9. November 1995 / Ley, Wilfried [Hrgs.]
Y1  - 1995
SN  - 3-922010-92-X
PB  - DGLR
CY  - Bonn
ER  - 
TY  - BOOK
A1  - Ley, Wilfried
T1  - Seilgefesselte Raumflugkörper, -Tethertechnik- : Gemeinschaftsveranstaltung der FH Aachen und der DGLR ... / 3. Raumfahrt-Kolloquium an der Fachhochschule Aachen, 13. Dezember 1990. [Wiss. Programmleitung: W. Ley, W. Hallmann]
Y1  - 1990
SN  - 3-922010-59-8
PB  - DGLR
CY  - Bonn
ER  - 
TY  - BOOK
A1  - Ley, Wilfried
T1  - Bewertung von Solarkollektormessungen unter natuerlichen und simulierten Bedingungen
Y1  - 1982
N1  - Deutsche Forschungs- und Versuchsanstalt für Luft- und Raumfahrt : Forschungsbericht ; 1982,5 ; zugl. Dissertation, Universität Bochum Abt. für Maschinenbau, 1981
PB  - Inst. f. Raumsimulation
CY  - Köln
ER  - 
TY  - BOOK
A1  - Ley, Wilfried
T1  - Handbuch der Raumfahrttechnik : Grundlagen - Nutzung, Raumfahrtsysteme - Produktsicherung u. Produktmanagement / Willi Hallmann; Wilfried Ley
Y1  - 1988
SN  - 3446151303
PB  - Hanser
CY  - München [u.a.]
ER  - 
TY  - BOOK
A1  - Ley, Wilfried
T1  - Handbuch der Raumfahrttechnik / Ley, Wilfried ; Wittmann, Klaus ; Hallmann, Willi [Hrsg.]
Y1  - 2008
SN  - 978-3-446-41185-2
PB  - Hanser
CY  - München
ER  - 
TY  - JOUR
A1  - Ley, Wilfried
A1  - Plescher, Engelbert
A1  - Scholz, Artur
A1  - Piepenbrock, Johannes
T1  - COMPASS-1 picosatellite project / Ley, Wilfried ; Plescher, Engelbert ; Scholz, Artur ; Piepenbrock, Johannes
JF  - Small satellites for earth observation : digest of the 6th International symposium of the International Academy of Astronautics, Berlin, April 23 - 26, 2007 / ed. by Rainer Sandau; Hans-Peter Röser; Arnoldo Valenzuela
Y1  - 2007
SN  - 9783896855718
N1  - Symposium on Small Satellites for Earth Observation ; (6, 2007, Berlin)
SP  - 147
EP  - 150
PB  - Wissenschaft und Technik Verl.
CY  - Berlin
ER  - 
TY  - BOOK
A1  - Ley, Wilfried
A1  - Wittmann, Klaus
A1  - Hallmann, Willi
T1  - Handbook of space technology
Y1  - 2009
SN  - 978-0-470-69739-9
PB  - Wiley
CY  - Chichester
ER  - 
TY  - CHAP
A1  - Loeb, Horst W.
A1  - Schartner, Karl-Heinz
A1  - Dachwald, Bernd
A1  - Ohndorf, Andreas
A1  - Seboldt, Wolfgang
T1  - An Interstellar – Heliopause mission using a combination of solar/radioisotope electric propulsion
T2  - Presented at the 32nd International Electric Propulsion Conference
N2  - 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.
Y1  - 2011
N1  - 32nd International Electric Propulsion Conference, 11-15 September. Wiesbaden, Germany
SP  - 1
EP  - 7
ER  -