Refine
Year of publication
- 2024 (2)
- 2023 (16)
- 2022 (12)
- 2021 (19)
- 2020 (29)
- 2019 (43)
- 2018 (23)
- 2017 (32)
- 2016 (26)
- 2015 (31)
- 2014 (13)
- 2013 (26)
- 2012 (12)
- 2011 (22)
- 2010 (24)
- 2009 (22)
- 2008 (19)
- 2007 (31)
- 2006 (31)
- 2005 (39)
- 2004 (21)
- 2003 (21)
- 2002 (21)
- 2001 (21)
- 2000 (16)
- 1999 (17)
- 1998 (15)
- 1997 (16)
- 1996 (8)
- 1995 (10)
- 1994 (12)
- 1993 (9)
- 1992 (10)
- 1991 (8)
- 1990 (15)
- 1989 (9)
- 1988 (9)
- 1987 (7)
- 1986 (1)
- 1985 (10)
- 1984 (6)
- 1983 (8)
- 1982 (3)
- 1979 (1)
- 1978 (1)
- 1977 (2)
Document Type
- Article (364)
- Conference Proceeding (192)
- Book (107)
- Part of a Book (43)
- Patent (19)
- Doctoral Thesis (10)
- Report (8)
- Other (3)
- Diploma Thesis (1)
- Master's Thesis (1)
- Poster (1)
Has Fulltext
- no (749) (remove)
Keywords
- avalanche (6)
- solar sail (5)
- hydrogen (4)
- snow (4)
- GOSSAMER-1 (3)
- Hydrogen (3)
- MASCOT (3)
- Wind Tunnel (3)
- Drinfeld modules (2)
- Flight Test (2)
- Mars (2)
- Micromix (2)
- NOx emissions (2)
- Pitching Moment (2)
- Solar sail (2)
- Spacecraft (2)
- Trajectory Optimization (2)
- Transcendence (2)
- Wave Drag (2)
- combustor development (2)
Institute
- Fachbereich Luft- und Raumfahrttechnik (749) (remove)
Handbook of space technology
(2009)
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.