MARS/EUROPA INPPS High Power Space Transportation

Paper number

IAC-19,A5,4-D2.8,9,x53118

Author

Dr. Frank Jansen, Germany, DLR (German Aerospace Center)

Coauthor

Mr. Benedikt Bergmann, Czech Republic, CTU in Prague

Coauthor

Dr. Tim Brandt, Czech Republic, CTU in Prague

Coauthor

Mr. Friedrich Damme, Germany, Technical University of Berlin

Coauthor

Dr. Emmanouil Detsis, France, European Science Foundation (ESF)

Coauthor

Mrs. Simona Ferraris, Italy, Thales Alenia Space Italia

Coauthor

Mr. James AP Findlay, United Kingdom, National Nuclear Laboratory

Coauthor

Dr. Ikkoh Funaki, Japan, JAXA/ISAS

Coauthor

Dr. Oliver Funke, Germany, Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR)

Coauthor

Mr. Jan Thimo Grundmann, Germany, DLR (German Aerospace Center)

Coauthor

Dr. Lamartine Nogueira Frutuoso Guimaraes, Brazil, Instituto de Estudos Avancados

Coauthor

Mr. Martin Hillebrandt, Germany, Deutsch Luft und Raumfahrt Zentrum (DLR)

Coauthor

Prof. A.C. Koroteev, Russian Federation, Keldych Research Centre

Coauthor

Dr. Daniel Kuehn, Germany, DFKI Robotics Innovation Center Bremen

Coauthor

Dr. Jim C. Kuijper, The Netherlands

Coauthor

Mr. Frederic Masson, France, Centre National d'Etudes Spatiales (CNES)

Coauthor

Dr. Volker Maiwald, Germany, Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR)

Coauthor

Prof. Jürgen Oberst, Germany, Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR)

Coauthor

Mr. Stephane Oriol, France, Centre National d'Etudes Spatiales (CNES)

Coauthor

Prof. Stanislav Pospisil, Czech Republic, Czech Technical University In Prague (CTU)

Coauthor

Mr. Martin Richter, Germany, DLR (German Aerospace Center)

Coauthor

Dr. Lars Schanz, Germany, DLR (German Aerospace Center)

Coauthor

Dr. Alexander V. Semenkin, Russian Federation, Keldych Research Centre

Coauthor

Dr. Alexander Solodukhin, Russian Federation, Keldych Research Centre

Coauthor

Prof. Ivan Stekl, Czech Republic, CTU in Prague

Coauthor

Mr. Tim Tinsley, United Kingdom, National Nuclear Laboratory

Coauthor

Dr. Maria Cristina Tosi, Italy, Thales Alenia Space

Coauthor

Dr. Christoph Waldmann, Germany, MARUM

Coauthor

Dr. Jean-Claude Worms, France, European Science Foundation

Year

2019

Abstract

This talk explicitly explains INPPS (International Nuclear Power and Propulsion System) flagship subsystems like nuclear reactor, shielding, power conversion, boom, radiators, building blocks for tanks / payload basket / PPU / cluster of electric thrusters as well as additional solar power ring electricity and real time radiation detectors. Differences between the two flagships - as high power space transportation tug - for non-human (second half of 2020th) Mars / Europa and human (2030th) Mars exploration missions are sketched.   

The international studied conditions for human Mars and exploration Europa space flights are realizable by rationales for pursuing high power space transportation by INPPS due to: 1) the successful finalization of the European-Russian DEMOCRITOS and MEGAHIT projects with their three concepts of space, ground and nuclear demonstrators for INPPS realization (reached in 2017), 2) the successful ground based test of the Russian nuclear reactor with 1MWel plus important heat transfer solution via droplet radiators (confirmed in 2018), 3) the space qualification of the Russian reactor until 2025 and 4) the perfect celestial constellation for a Earth-Mars/Phobos-Earth-Jupiter/Europa trajectory in 2026-2031 for maximal INPPS flagship tests. Critical performance will be studied by parallel realizations of the ground and nuclear demonstrators of DEMOCRITOS (until 2025). The space qualification of INPPS with all subsystems including the nuclear reactor in the middle of the 2020th plus the INPPS tests for about one to two years – first in high Earth orbit robotic assembly phase of INPPS and later extended in nearby Earth space environment flight - means a complete concepts driven approval for all applied INPPS space technologies for both Mars/Europa exploration missions by INPPS flagship.   

In dependence – from the cluster of electric thrusters - the MARS/EUROPA INPPS payload mass is up to 18/12 tons. This very high payload mass allows to transport scientific, pure commercial and new media communication payload sections. For example, the scientific payload also includes a small INPPS orbiting inspection satellite. The INPPS flagship missions are visionary, comparable with Apollo project and ISS with dedicated outcomes for science / technologies, international peaceful cooperation in space and additionally for commercialization plus communication from space to Earth, means in space down to Earth.

Abstract document

IAC-19,A5,4-D2.8,9,x53118.brief.pdf

Manuscript document

IAC-19,A5,4-D2.8,9,x53118.pdf (🔒 authorized access only).

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