152 results on '"Grundmann, Jan Thimo"'
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2. ASIME 2018 White Paper. In-Space Utilisation of Asteroids: Asteroid Composition -- Answers to Questions from the Asteroid Miners
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Graps, Amara L., Abbud-Madrid, Angel, Abell, Paul, Barucci, Antonella, Beck, Pierre, Bonal, Lydie, Bonin, Grant, Borgersen, Øystein Risan, Britt, Daniel, Campins, Humberto, Cannon, Kevin, Carnelli, Ian, Carry, Benoît, Crawford, Ian, de Leon, Julia, Drube, Line, Donaldson-Hanna, Kerri, Elvis, Martin, Fitzsimmons, Alan, Galache, JL, Green, Simon F., Grundmann, Jan Thimo, Herique, Alan, Hestroffer, Daniel, Hsieh, Henry, Kereszturi, Akos, Kueppers, Michael, Lewicki, Chris, Lin, Yangting, Mainzer, Amy, Michel, Patrick, Moon, Hong-Kyu, Nakamura, Tomoki, Penttila, Antti, Pursiainen, Sampsa, Raymond, Carol, Reddy, Vishnu, Rivkin, Andy, Sercel, Joel, Stickle, Angela, Tanga, Paolo, Takala, Mika, Wirtz, Tom, and Wu, YunZhao
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Astrophysics - Earth and Planetary Astrophysics - Abstract
In keeping with the Luxembourg government's initiative to support the future use of space resources, ASIME 2018 was held in Belval, Luxembourg on April 16-17, 2018. The goal of ASIME 2018: Asteroid Intersections with Mine Engineering, was to focus on asteroid composition for advancing the asteroid in-space resource utilisation domain. What do we know about asteroid composition from remote-sensing observations? What are the potential caveats in the interpretation of Earth-based spectral observations? What are the next steps to improve our knowledge on asteroid composition by means of ground-based and space-based observations and asteroid rendez-vous and sample return missions? How can asteroid mining companies use this knowledge? ASIME 2018 was a two-day workshop of almost 70 scientists and engineers in the context of the engineering needs of space missions with in-space asteroid utilisation. The 21 Questions from the asteroid mining companies were sorted into the four asteroid science themes: 1) Potential Targets, 2) Asteroid-Meteorite Links, 3) In-Situ Measurements and 4) Laboratory Measurements. The Answers to those Questions were provided by the scientists with their conference presentations and collected by A. Graps or edited directly into an open-access collaborative Google document or inserted by A. Graps using additional reference materials. During the ASIME 2018, first day and second day Wrap-Ups, the answers to the questions were discussed further. New readers to the asteroid mining topic may find the Conversation boxes and the Mission Design discussions especially interesting., Comment: Outcome from the ASIME 2018: Asteroid Intersections with Mine Engineering, Luxembourg. April 16-17, 2018. 65 Pages. arXiv admin note: substantial text overlap with arXiv:1612.00709
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- 2019
3. The MMX rover: performing in situ surface investigations on Phobos
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Michel, Patrick, Ulamec, Stephan, Böttger, Ute, Grott, Matthias, Murdoch, Naomi, Vernazza, Pierre, Sunday, Cecily, Zhang, Yun, Valette, Rudy, Castellani, Romain, Biele, Jens, Tardivel, Simon, Groussin, Olivier, Jorda, Laurent, Knollenberg, Jörg, Grundmann, Jan Thimo, Arrat, Denis, Pont, Gabriel, Mary, Stephane, Grebenstein, Markus, Miyamoto, Hirdy, Nakamura, Tomoki, Wada, Koji, Yoshikawa, Kent, and Kuramoto, Kiyoshi
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- 2022
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4. ASIME 2016 White Paper: In-Space Utilisation of Asteroids: 'Answers to Questions from the Asteroid Miners'
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Graps, Amara L., Blondel, Philippe, Bonin, Grant, Britt, Daniel, Centuori, Simone, Delbo, Marco, Drube, Line, Duffard, Rene, Elvis, Martin, Faber, Daniel, Frank, Elizabeth, Galache, JL, Green, Simon F., Grundmann, Jan Thimo, Hsieh, Henry, Kereszturi, Akos, Laine, Pauli, Levasseur-Regourd, Anny-Chantal, Maier, Philipp, Metzger, Philip, Michel, Patrick, Mueller, Migo, Mueller, Thomas, Murdoch, Naomi, Parker, Alex, Pravec, Petr, Reddy, Vishnu, Sercel, Joel, Rivkin, Andy, Snodgrass, Colin, and Tanga, Paolo
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Astrophysics - Earth and Planetary Astrophysics - Abstract
The aim of the Asteroid Science Intersections with In-Space Mine Engineering (ASIME) 2016 conference on September 21-22, 2016 in Luxembourg City was to provide an environment for the detailed discussion of the specific properties of asteroids, with the engineering needs of space missions that utilize asteroids. The ASIME 2016 Conference produced a layered record of discussions from the asteroid scientists and the asteroid miners to understand each other's key concerns and to address key scientific questions from the asteroid mining companies: Planetary Resources, Deep Space Industries and TransAstra. These Questions were the focus of the two day conference, were addressed by scientists inside and outside of the ASIME Conference and are the focus of this White Paper. The Questions from the asteroid mining companies have been sorted into the three asteroid science themes: 1) survey, 2) surface and 3) subsurface and 4) Other. The answers to those Questions have been provided by the scientists with their conference presentations or edited directly into an early open-access collaborative Google document (August 2016-October 2016), or inserted by A. Graps using additional reference materials. During the ASIME 2016 last two-hours, the scientists turned the Questions from the Asteroid Miners around by presenting their own key concerns: Questions from the Asteroid Scientists . These answers in this White Paper will point to the Science Knowledge Gaps (SKGs) for advancing the asteroid in-space resource utilisation domain., Comment: 81 pages, 18 figures. White Paper from the Asteroid Science Intersections with In-Space Mine Engineering (ASIME) 2016 conference on September 21-22, 2016 in Luxembourg City
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- 2016
5. The MASCOT lander aboard Hayabusa2: The in-situ exploration of NEA (162173) Ryugu
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Ho, Tra-Mi, Jaumann, Ralf, Bibring, Jean-Pierre, Grott, Matthias, Glaßmeier, Karl-Heinz, Moussi, Aurelie, Krause, Christian, Auster, Ulrich, Baturkin, Volodymyr, Biele, Jens, Cordero, Federico, Cozzoni, Barbara, Dudal, Clement, Fantinati, Cinzia, Grimm, Christian, Grundmann, Jan-Thimo, Hamm, Maximilian, Herčik, David, Kayal, Kağan, Knollenberg, Jörg, Küchemann, Oliver, Ksenik, Eugen, Lange, Caroline, Lange, Michael, Lorda, Laurence, Maibaum, Michael, Mimasu, Yuya, Cenac-Morthe, Celine, Okada, Tatsuaki, Otto, Katharina, Pilorget, Cedric, Reill, Josef, Saiki, Takanao, Sasaki, Kaname, Schlotterer, Markus, Schmitz, Nicole, Schröder, Stefan, Termtanasombat, Nawarat, Toth, Nortbert, Tsuda, Yuichi, Ulamec, Stephan, Wolff, Friederike, Yoshimitsu, Tetsuo, and Ziach, Christan
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- 2021
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6. Paths not taken – The Gossamer roadmap’s other options
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Spietz, Peter, Spröwitz, Tom, Seefeldt, Patric, Grundmann, Jan Thimo, Jahnke, Rico, Mikschl, Tobias, Mikulz, Eugen, Montenegro, Sergio, Reershemius, Siebo, Renger, Thomas, Ruffer, Michael, Sasaki, Kaname, Sznajder, Maciej, Tóth, Norbert, Ceriotti, Matteo, Dachwald, Bernd, Macdonald, Malcolm, McInnes, Colin, Seboldt, Wolfgang, Quantius, Dominik, Bauer, Waldemar, Wiedemann, Carsten, Grimm, Christian D., Herčík, David, Ho, Tra-Mi, Lange, Caroline, and Schmitz, Nicole
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- 2021
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7. Sailing at the brink – The no-limits of near-/now-term-technology solar sails and SEP spacecraft in (multiple) NEO rendezvous
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Ceriotti, Matteo, Viavattene, Giulia, Moore, Iain, Peloni, Alessandro, McInnes, Colin R., and Grundmann, Jan Thimo
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- 2021
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8. Performance analysis and mission applications of a new solar sail concept based on crossed booms with tip-deployed membranes
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Seefeldt, Patric, Grundmann, Jan Thimo, Hillebrandt, Martin, and Zander, Martin
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- 2021
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9. DLR Reusability Flight Experiment ReFEx
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Bauer, Waldemar, Rickmers, Peter, Kallenbach, Alexander, Stappert, Sven, Wartemann, Viola, Hans-Joachim Merrem, Clemens, Schwarz, René, Sagliano, Marco, Grundmann, Jan Thimo, Flock, Andreas, Thiele, Thomas, Kiehn, Daniel, Bierig, Andreas, Windelberg, Jens, Ksenik, Eugen, Bruns, Thorben, Ruhe, Tobias, and Elsäßer, Henning
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- 2020
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10. The MASCOT separation mechanism: A reliable, low-mass deployment system for nano-spacecraft
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Grimm, Christian D., Lange, Caroline, Lange, Michael, Mierheim, Olaf, Witte, Lars, Sasaki, Kaname, Chand, Suditi, Ksenik, Eugen, Grundmann, Jan-Thimo, Ho, Tra-Mi, Biele, Jens, Hercik, David, Auster, Uli, Lorda, Laurence, Torres, Alex, and Garmier, Romain
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- 2020
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11. Concept for a Gossamer solar power array using thin-film photovoltaics
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Sproewitz, Tom, Banik, Udayan, Grundmann, Jan-Thimo, Haack, Frederik, Hillebrandt, Martin, Martens, Hauke, Meyer, Sebastian, Reershemius, Siebo, Reininghaus, Nies, Sasaki, Kaname, Seefeldt, Patric, Sergeev, Oleg, Spietz, Peter, Sznajder, Maciej, Toth, Norbert, Vehse, Martin, Wippermann, Torben, and Zander, Martin E.
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- 2020
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12. A radar package for asteroid subsurface investigations: Implications of implementing and integration into the MASCOT nanoscale landing platform from science requirements to baseline design
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Herique, Alain, Plettemeier, Dirk, Lange, Caroline, Grundmann, Jan Thimo, Ciarletti, Valerie, Ho, Tra-Mi, Kofman, Wlodek, Agnus, Benoit, Du, Jun, Fa, Wenzhe, Gassot, Oriane, Granados-Alfaro, Ricardo, Grygorczuk, Jerzy, Hahnel, Ronny, Hoarau, Christophe, Laabs, Martin, Le Gac, Christophe, Mütze, Marco, Rochat, Sylvain, Rogez, Yves, Tokarz, Marta, Schaffer, Petr, Vieau, André-Jean, Biele, Jens, Buck, Christopher, Gil Fernandez, Jesus, Krause, Christian, Suquet, Raquel Rodriguez, and Ulamec, Stephan
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- 2019
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13. Capabilities of Gossamer-1 derived small spacecraft solar sails carrying Mascot-derived nanolanders for in-situ surveying of NEAs
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Grundmann, Jan Thimo, Bauer, Waldemar, Biele, Jens, Boden, Ralf, Ceriotti, Matteo, Cordero, Federico, Dachwald, Bernd, Dumont, Etienne, Grimm, Christian D., Herčík, David, Ho, Tra-Mi, Jahnke, Rico, Koch, Aaron D., Koncz, Alexander, Krause, Christian, Lange, Caroline, Lichtenheldt, Roy, Maiwald, Volker, Mikschl, Tobias, Mikulz, Eugen, Montenegro, Sergio, Pelivan, Ivanka, Peloni, Alessandro, Quantius, Dominik, Reershemius, Siebo, Renger, Thomas, Riemann, Johannes, Ruffer, Michael, Sasaki, Kaname, Schmitz, Nicole, Seboldt, Wolfgang, Seefeldt, Patric, Spietz, Peter, Spröwitz, Tom, Sznajder, Maciej, Tardivel, Simon, Tóth, Norbert, Wejmo, Elisabet, Wolff, Friederike, and Ziach, Christian
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- 2019
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14. MASCOT2 – A small body lander to investigate the interior of 65803 Didymos′ moon in the frame of the AIDA/AIM mission
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Lange, Caroline, Biele, Jens, Ulamec, Stephan, Krause, Christian, Cozzoni, Barbara, Küchemann, Oliver, Tardivel, Simon, Ho, Tra-Mi, Grimm, Christian, Grundmann, Jan Thimo, Wejmo, Elisabet, Schröder, Silvio, Lange, Michael, Reill, Josef, Hérique, Alain, Rogez, Yves, Plettemeier, Dirk, Carnelli, Ian, Galvez, Andrés, Philippe, Christian, Küppers, Michael, Grieger, Björn, Fernandez, Jesus Gil, Grygorczuk, Jerzy, Tokarz, Marta, and Ziach, Christian
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- 2018
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15. Gossamer-1: Mission concept and technology for a controlled deployment of gossamer spacecraft
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Seefeldt, Patric, Spietz, Peter, Sproewitz, Tom, Grundmann, Jan Thimo, Hillebrandt, Martin, Hobbie, Catherin, Ruffer, Michael, Straubel, Marco, Tóth, Norbert, and Zander, Martin
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- 2017
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16. Gossamer Roadmap Technology Reference Study for a Multiple NEO Rendezvous Mission
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Dachwald, Bernd, Boehnhardt, Hermann, Broj, Ulrich, Geppert, Ulrich R. M. E., Grundmann, Jan-Thimo, Seboldt, Wolfgang, Seefeldt, Patric, Spietz, Peter, Johnson, Les, Kührt, Ekkehard, Mottola, Stefano, Macdonald, Malcolm, McInnes, Colin R., Vasile, Massimiliano, Reinhard, Ruedeger, and Macdonald, Malcolm, editor
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- 2014
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17. Asteroid Ryugu before the Hayabusa2 encounter
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Wada, Koji, Grott, Matthias, Michel, Patrick, Walsh, Kevin J., Barucci, Antonella M., Biele, Jens, Blum, Jürgen, Ernst, Carolyn M., Grundmann, Jan Thimo, Gundlach, Bastian, Hagermann, Axel, Hamm, Maximilian, Jutzi, Martin, Kim, Myung-Jin, Kührt, Ekkehard, Le Corre, Lucille, Libourel, Guy, Lichtenheldt, Roy, Maturilli, Alessandro, Messenger, Scott R., Michikami, Tatsuhiro, Miyamoto, Hideaki, Mottola, Stefano, Müller, Thomas, Nakamura, Akiko M., Nittler, Larry R., Ogawa, Kazunori, Okada, Tatsuaki, Palomba, Ernesto, Sakatani, Naoya, Schröder, Stefan E., Senshu, Hiroki, Takir, Driss, Zolensky, Michael E., and International Regolith Science Group (IRSG) in Hayabusa2 project
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- 2018
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18. Spacecraft for Hypervelocity Impact Research – An Overview of Capabilities, Constraints and the Challenges of Getting There
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Grundmann, Jan Thimo, Dachwald, Bernd, Grimm, Christian D., Kahle, Ralph, Koch, Aaron Dexter, Krause, Christian, Lange, Caroline, Quantius, Dominik, and Ulamec, Stephan
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- 2015
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19. MASCOT—The Mobile Asteroid Surface Scout Onboard the Hayabusa2 Mission
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Ho, Tra-Mi, Baturkin, Volodymyr, Grimm, Christian, Grundmann, Jan Thimo, Hobbie, Catherin, Ksenik, Eugen, Lange, Caroline, Sasaki, Kaname, Schlotterer, Markus, Talapina, Maria, Termtanasombat, Nawarat, Wejmo, Elisabet, Witte, Lars, Wrasmann, Michael, Wübbels, Guido, Rößler, Johannes, Ziach, Christian, Findlay, Ross, Biele, Jens, Krause, Christian, Ulamec, Stephan, Lange, Michael, Mierheim, Olaf, Lichtenheldt, Roy, Maier, Maximilian, Reill, Josef, Sedlmayr, Hans-Jürgen, Bousquet, Pierre, Bellion, Anthony, Bompis, Olivier, Cenac-Morthe, Celine, Deleuze, Muriel, Fredon, Stephane, Jurado, Eric, Canalias, Elisabet, Jaumann, Ralf, Bibring, Jean-Pierre, Glassmeier, Karl Heinz, Hercik, David, Grott, Matthias, Celotti, Luca, Cordero, Federico, Hendrikse, Jeffrey, and Okada, Tatsuaki
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- 2017
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20. Probes to the inferior planets—A new dawn for NEO and IEO detection technology demonstration from heliocentric orbits interior to the earth's?
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Grundmann, Jan Thimo, Mottola, Stefano, Drentschew, Maximilian, Drobczyk, Martin, Kahle, Ralph, Maiwald, Volker, Quantius, Dominik, Zabel, Paul, and van Zoest, Tim
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- 2013
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21. A space-based mission to characterize the IEO population
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Findlay, Ross, Eßmann, Olaf, Grundmann, Jan Thimo, Hoffmann, Harald, Kührt, Ekkehard, Messina, Gabriele, Michaelis, Harald, Mottola, Stefano, Müller, Hartmut, and Pedersen, Jakob Fromm
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- 2013
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22. MASCOT—A Mobile Lander On-board the Hayabusa2 Spacecraft—Operations on Ryugu
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Krause, Christian, Auster, H.U., Bibring, J.-P., Biele, Jens, Cenac-Morthe, Céline, Cordero, Federico, Cozzoni, Barbara, Dudal, Clement, Embacher, Daniel, Fantinati, Cinizia, Fischer, Hans-Herbert, Glassmeier, K. H., Granena, David, Grott, Matthias, Grundmann, Jan Thimo, Hamm, V., Hercik, D., Ho, Tra-Mi, Jaumann, Ralf, Kayal, Kagan, Knollenberg, Jörg, Küchemann, Oliver, Lange, Caroline, Lorda, Laurence, Maibaum, Michael, May, Daniel, Mimasu, Yuya, Moussi-Souffys, Aurélie, Okada, T., Reill, Josef, Saiki, Takanao, Sasaki, Kaname, Schlotterer, Markus, Schmitz, Nicole, Toth, Norbert, Tsuda, Yuichi, Ulamec, Stephan, Yoshimitsu, Tetsuo, Watanabe, S., and Wolff, Friederike
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Landing ,Surface ,MASCOT ,Asteroid ,Ryugu ,Hayabusa2 - Published
- 2022
23. Magnetic Properties of Asteroid (162173) Ryugu
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Massachusetts Institute of Technology. Department of Earth, Atmospheric, and Planetary Sciences, Hercik, David, Auster, Hans-Ulrich, Constantinescu, Dragos, Blum, Jürgen, Fornaçon, Karl-Heinz, Fujimoto, Masaki, Gebauer, Kathrin, Grundmann, Jan-Thimo, Güttler, Carsten, Hillenmaier, Olaf, Ho, Tra-Mi, Hördt, Andreas, Krause, Christian, Kührt, Ekkehard, Lorda, Laurence, Matsuoka, Ayako, Motschmann, Uwe, Moussi-Soffys, Aurélie, Richter, Ingo, Sasaki, Kaname, Scholten, Frank, Stoll, Bernd, Weiss, Benjamin P., Wolff, Friederike, Glassmeier, Karl-Heinz, Massachusetts Institute of Technology. Department of Earth, Atmospheric, and Planetary Sciences, Hercik, David, Auster, Hans-Ulrich, Constantinescu, Dragos, Blum, Jürgen, Fornaçon, Karl-Heinz, Fujimoto, Masaki, Gebauer, Kathrin, Grundmann, Jan-Thimo, Güttler, Carsten, Hillenmaier, Olaf, Ho, Tra-Mi, Hördt, Andreas, Krause, Christian, Kührt, Ekkehard, Lorda, Laurence, Matsuoka, Ayako, Motschmann, Uwe, Moussi-Soffys, Aurélie, Richter, Ingo, Sasaki, Kaname, Scholten, Frank, Stoll, Bernd, Weiss, Benjamin P., Wolff, Friederike, and Glassmeier, Karl-Heinz
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©2020. The Authors. Observations of the magnetization state of asteroids indicate diverse properties. Values between 1.9 × 10 -6Am2/kg (Eros) and 10-2 Am2/kg (Braille) have been reported. A more detailed understanding of asteroidal magnetic properties allows far-reaching conclusions of the magnetization mechanism as well as the strength of the magnetic field of the solar system regions the asteroid formed in. The Hayabusa2 mission with its lander Mobile Asteroid Surface Scout is equipped with a magnetometer experiment, MasMag. MasMag is a state-of-the-art three-axis fluxgate magnetometer, successfully operated also on Philae, the Rosetta mission lander. MasMag has enabled, after Eros for the second time ever, to determine the magnetic field of an asteroid during descent and on-surface operations. The new observations show that Ryugu, a low-albedo C-type asteroid, has no detectable global magnetization, and any local magnetization is either small (< 10−6 Am2/kg) or on very small (subcentimeter) scales. This implies, for example, that energetic solar wind particles could reach and alter the surface unimpeded by strong asteroidal magnetic fields, such as minimagnetospheres in case of the Moon.
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- 2022
24. MASCOT—The Mobile Asteroid Surface Scout Onboard the Hayabusa2 Mission
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Ho, Tra-Mi, primary, Baturkin, Volodymyr, additional, Grimm, Christian, additional, Grundmann, Jan Thimo, additional, Hobbie, Catherin, additional, Ksenik, Eugen, additional, Lange, Caroline, additional, Sasaki, Kaname, additional, Schlotterer, Markus, additional, Talapina, Maria, additional, Termtanasombat, Nawarat, additional, Wejmo, Elisabet, additional, Witte, Lars, additional, Wrasmann, Michael, additional, Wübbels, Guido, additional, Rößler, Johannes, additional, Ziach, Christian, additional, Findlay, Ross, additional, Biele, Jens, additional, Krause, Christian, additional, Ulamec, Stephan, additional, Lange, Michael, additional, Mierheim, Olaf, additional, Lichtenheldt, Roy, additional, Maier, Maximilian, additional, Reill, Josef, additional, Sedlmayr, Hans-Jürgen, additional, Bousquet, Pierre, additional, Bellion, Anthony, additional, Bompis, Olivier, additional, Cenac-Morthe, Celine, additional, Deleuze, Muriel, additional, Fredon, Stephane, additional, Jurado, Eric, additional, Canalias, Elisabet, additional, Jaumann, Ralf, additional, Bibring, Jean-Pierre, additional, Glassmeier, Karl Heinz, additional, Hercik, David, additional, Grott, Matthias, additional, Celotti, Luca, additional, Cordero, Federico, additional, Hendrikse, Jeffrey, additional, and Okada, Tatsuaki, additional
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- 2016
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25. Non-Human + Human Deep Space Exploration: By The NEP INPPS Flagship
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Jansen, Frank, Bittner, Michael, Damme, Friedrich, Ehresmann, Manfred, Funke, Oliver, Grill, Julia, Grundmann, Jan Thimo, Herdrich, Georg, Hillebrandt, Martin, Leiter, Hans, Maiwald, Volker, Oberst, Jürgen, Richter, Martin, Reynders, Martin, Schanz, Lars, Schmidt-Tedd, Bernhard, Wüst, Sabine, Detsis, Emmanouil, Masson, Frederic, Oriol, Stephane, Girard, Nathalie, Worms, Jean-Claude, Ferraris, Simona, Tosi, Cristina Maria, Cesaretti, Giovanni, Piragino, Antonio, Andreussi, Tommaso, Misuri, Tommaso, Reissner, Alexander, Krejci, David, Kuijper, Jim C., Bergmann, Benedikt, Pospisil, Stanislav, Stekl, Ivan, Brandt, Tim, Koroteev, Anatoly S., Semenkin, Alexander V., Solodukhin, Alexander E., Popov, Garri A., Petrukovich, A., Starinova, Olga, Rozhkov, Miroslav, Price, Colin, Funaki, Ikkoh, Tinslay, Tim, and Nogueira Frutuoso Guimaraes, Lamartine
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crewed spaceflight ,telepresence ,INPPS ,NEP ,International ,Exploration - Published
- 2021
26. Humans to Mars: by MARS- plus EUROPA-INPPS Flagship Mission
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Jansen, Frank, Andreussi, Tommaso, Bergmann, Benedikt, Bittner, Michael, Brandt, Tim, Cesarretti, Giovanni, Damme, Friedrich, Ehresmann, Manfred, Herdrich, Georg, Detsis, Emmanouil, Ferraris, Simona, Funaki, Ikkoh, Funke, Oliver, Girard, Nathalie, Grundmann, Jan Thimo, Nogueira Frutuoso Guimaraes, Lamartine, Hillebrandt, Martin, Koroteev, Anatoly S., Krejci, David, Kuijper, Jim C., Leiter, Hans, Masson, Frederic, Maiwald, Volker, Misuri, Tommaso, Oberst, Jürgen, Oriol, Stephane, Piragino, Antonio, Petukhov, Viacheslav, Popov, Garri A., Pospisil, Stanislav, Price, Colin, Richter, Martin, Reissner, Alexander, Reynders, Martin, Rozhkov, Miroslav, Schanz, Lars, Schmidt-Tedd, Bernhard, Semenkin, Alexander V., Solodukhin, Alexander E., Starinova, Olga, Stekl, Ivan, Tinsley, Tim, Tosi, Maria Cristina, Worms, Jean-Claude, and Wüst, Sabine
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crewed spaceflight ,telepresence ,Mars (planet) ,INPPS (International Nuclear Power and Propulsion System) flagship ,Europa (moon) ,nuclear-electric propulsion ,DEMOCRITOS ,MEGAHIT - Published
- 2021
27. More Bucks for the Bang: New Space Solutions, Impact Tourism and one Unique Science & Engineering Opportunity at T-6 Months and Counting
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Grundmann, Jan Thimo, Borella, Laura, Ceriotti, Matteo, Chand, Suditi, Cordero, Federico, Dachwald, Bernd, Fexer, Sebastian, Fuglesang, Christer, Garcia de Herreros Miciano, María, Grimm, Christian, Hendrikse, Jeffrey, Hercik, David, Herique, Alain, Hillebrandt, Martin, Ho, Tra-Mi, Kesseler, Lars, Laabs, M., Lange, Caroline, Lange, Michael, Lichtenheldt, Roy, Nyman, Erik Lindblad, McInnes, Colin, Moore, Iain, Peloni, Alessandro, Plettemeier, Dirk, Quantius, Dominik, Ricci, Leonardo, Seefeldt, Patric, Tibert, Gunnar, Venditti, Flaviane C. F., Vergaaij, Merel, Vial, Simon, Viavattene, Giulia, Virkki, Anne K., Wu, Jingyang, and Zander, Martin E.
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Near-Earth Object ,new space ,responsive space ,disaster preparedness ,hazardous asteroid mitigation - Published
- 2021
28. Planetary Defense Ground Zero: MASCOT's View on the Rocks - an Update between First Images and Sample Return
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Ho, Tra-Mi, Jaumann, Ralf, Bibring, J.-P., Grott, Matthias, Glaßmeier, K.H. (4), Moussi-Soffys, A., Krause, Christian, Auster, Hans-Ulrich, Baturkin, Volodymyr, Biele, Jens, Cordero, Federico, Cozzoni, Barbara, Dudal, Clement, Fantinati, C., Grimm, Christian, Grundmann, Jan Thimo, Hamm, Maximilian, Hendrikse, Jeffrey, Hercik, David, Kayal, Kagan, Knollenberg, Jörg, Küchemann, Oliver, Lange, Caroline, Lange, Michael, Lorda, Laurence, Maibaum, Michael, Mimasu, Yuya, Cenac-Morthe, Céline, Okada, T., Otto, Katharina A., Pilorget, C., Reill, Josef, Saiki, Takanao, Sasaki, Kaname, Schlotterer, Markus, Schmitz, Nicole, Schröder, Stefan, Termtanasombat, Nawarat, Toth, Norbert, Tsuda, Y., Ulamec, S., Wolff, Friederike, Yoshimitsu, T., Ziach, Christian, the MASCOT team, the MASCOT team, Ailor, William H, Barbee, Brent, Drolshagen, Gerhard, Karl, Alex, Melamed, Nahum, and Brozovic, Marina
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Funktionsleichtbau ,(162173) Ryugu ,asteroid surface properties ,MASCOT ,Systementwicklung und Projektbüro ,Nutzerzentrum für Weltraumexperimente (MUSC) ,Mechatronische Systeme ,Planetengeologie ,Planetenphysik ,Avioniksysteme ,Land und Explorationstechnologie ,Planetare Sensorsysteme ,HAYABUSA2 ,Mechanik und Thermalsysteme ,planetary defense - Abstract
At 01:57:20 UTC on October 3rd, 2018, after 3½ years of cruise aboard the JAXA spacecraft HAYABUSA2 and about 3 months in the vicinity of its target, the MASCOT lander was separated successfully by from an altitude of 41 m. After a free-fall of only ~5m51s MASCOT made first contact with C-type near-Earth and potentially hazardous asteroid (162173) Ryugu, by hitting a big boulder. MASCOT then bounced for ~11m3s, in the process already gathering valuable information on mechanical properties of the surface before it came to rest. It was able to perform science measurements at 3 different locations on the surface of Ryugu and took many images of its spectacular pitch-black landscape. MASCOT’s payload suite was designed to investigate the fine-scale structure, multispectral reflectance, thermal characteristics and magnetic properties of the surface. Somewhat unexpectedly, MASCOT encountered very rugged terrain littered with large surface boulders. Observing in-situ, it confirmed the absence of fine particles and dust as already implied by the remote sensing instruments aboard the HAYABUSA2 spacecraft. After some 17h of operations, MASCOT‘s mission ended with the last communication contact as it followed Ryugu’s rotation beyond the horizon as seen from HAYABUSA2. Soon after, its primary battery was depleted. We present a broad overview of the recent scientific results of the MASCOT mission from separation through descent, landing and in-situ investigations on Ryugu until the end of its operation and relate them to the needs of planetary defense interactions with asteroids. We also recall the agile, responsive and sometimes serendipitous creation of MASCOT, the two-year rush of building and delivering it to JAXA’s HAYABUSA2 spacecraft in time for launch, and the four years of in-flight operations and on-ground testing to make the most of the brief on-surface mission.
- Published
- 2021
29. How we beat 2019 PDC to NYC by 2 years, within 2 years, 2 years ago
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Ceriotti, Matteo, Seefeldt, Patric, Kesseler, Lars, Viavattene, Giulia, Moore, Iain, Peloni, Alessandro, McInnes, Colin, Hillebrandt, Martin, Zander, Martin E., Grundmann, Jan Thimo, Lange, Caroline, Ailor, William H, Barbee, Brent, Drolshagen, Gerhard, Karl, Alex, Melamed, Nahum, Cheng, A.F., Tantardini, Marco, and Vardaxis, George
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Funktionsleichtbau ,small spacecraft ,Near-Earth Object ,Systementwicklung und Projektbüro ,solar sail ,Mechanik und Thermalsysteme ,Membrane deployment strategies ,Solar-Electric propulsion - Abstract
For the Planetary Defense Conference Exercise 2019, we set out to find ways to obtain the earliest possible characterization of the incoming (fictitious!) asteroid, 2019 PDC. After a partially successful deflection, a 'small' fragment was still bound for impact. The location was only known two weeks before impact - the time left for the evacuation of the larger New York City metropolitan region. With experience in Near-Earth Object (NEO) exploration mission design, solar sail and solar-electric propulsion (SEP) technology for small spacecraft, agile responsive design and integration, and from previous PDC Exercises, the importance of earliest possible information on impact location and energy was obvious. NEO in-situ exploration can provide invaluable information not just for deflection actions but also for planetary science and resource utilization. This is only possible with space missions closely approaching the asteroid. Expecting a solar sail mission flying in the 2020s could be re-directed, a unique feature of solar sailing, we searched for multiple rendezvous missions at initial sail technology characteristic accelerations of =2 years, within
- Published
- 2021
30. MASCOT Asteroid Nanolanders: From Ryugu and Didymoon towards Future Missions at ‘2021 PDC’, Apophis 2029, and Beyond
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Lange, Caroline, Ho, Tra-Mi, Grundmann, Jan Thimo, Borella, Laura, Chand, Suditi, Cordero, Federico, Fexer, Sebastian, Grimm, Christian, Hendrikse, Jeffrey, Hercik, David, Herique, Alain, Kesseler, Lars, Laabs, M., Lange, Michael, Lichtenheldt, Roy, Plettemeier, D., Quantius, Dominik, Venditti, Flaviane C. F., Virkki, Anne K., Ailor, William H, Barbee, Brent, Drolshagen, Gerhard, Karl, Alex, Melamed, Nahum, Cheng, Andy, Tantardini, Marco, and Vardaxis, George
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Funktionsleichtbau ,Raumfahrt-Systemdynamik ,Near-Earth Object ,nanolander ,re-use strategies ,Land und Explorationstechnologie ,Systementwicklung und Projektbüro ,planetary science radar ,Systemanalyse Raumsegment ,MASCOT2 - Abstract
For now, the Planetary Defense Conference Exercise 2021's incoming fictitious(!) asteroid, 2021 PDC, seems headed for impact on October 20th, 2021, exactly 6 months after its discovery. Today (Monday, April 26th, 2021), the impact probability is 5%, in a steep rise from 1 in 2500 upon discovery six days ago. We all know how these things end. Or do we? Unless somebody wants to keep civil defense very busy very soon, the chance is 95% that it will not hit; instead fly by closely to Earth, swing by to a new orbit that takes it away essentially forever or back again sooner or later through a keyhole, for a re-play at different odds. This is where our story starts and the story sounds familiar: season's greetings from 2004 MN4, now better known as (99942) Apophis. One more thing is similar: the close fly-by is an easy launch opportunity to 'jump aboard' that potentially hazardous asteroid for planetary science and tracking of longterm Yarkovsky-shifted keyhole resonant return risks. Indeed, missions are currently being discussed to launch during the 2029 fly-by of Apophis to rendezvous and investigate it closely right after. Others strive for an earlier launch to rendezvous well before, to observe all of the close fly-by at Earth and what it might do to a likely delicate rubble pile asteroid. Presently, this is an unlikely if not impossible option for sudden encounters like 2021 PDC with a lead time of months. But when asteroid mining (...possibly the other ...-not-if of asteroids?) takes off in the same manner as low Earth orbit communications satellites, this option may become a reality. But for now, even if a suitable planetary mission were serendipitously ready atop a suitable launch vehicle, could you get it an asteroid lander within 6 months? Surprisingly, this option existed between late 2014 and late 2018 when the MASCOT Qualification Model turned Flight Spare was kept fully integrated and flight ready for on-ground testing to prepare for the Flight Model's brief but complete mission on Ryugu with JAXA's highly successful HAYABUSA2 probe. At the same time, the MASCOT2 detailed design study for ESA's former AIM mission within the common NASA-ESA AIDA mission to (65803) Didymos and its moonlet, Dimorphos (then affectionately known as 'Didymoon'), paved the way for long-life MASCOTs, many of which have been discussed and studied since. The thoughtful design of MASCOT’s hardware and software allowed for a very high degree of re-use and flexibility regarding scientific payloads. MASCOT2 was to investigate the interior of Didymoon by Low-Frequency Radar. Close encounters like Apophis' offer unique opportunities for Earth-based planetary radar assets to work with spacecraft near and landers on the passing asteroid. We present a range of options for radar- and composition-oriented long-life MASCOT variants - to be delivered to the surfaces of the respective asteroid bodies - for the presently most likely near miss of 2021 PDC and the most certain close fly-by of (99942) Apophis on Friday, April 13th, 2029.
- Published
- 2021
31. Mars- plus Europa-INPPS Flagship Missions with High Power Electric Thrusters and Heavy Science Payload
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Jansen, Frank, Bittner, Michael, Damme, Friedrich, Ehresmann, Manfred, Funke, Oliver, Grill, Julia, Grundmann, Jan Thimo, Herdrich, Georg, Hillebrandt, Martin, Leiter, Hans, Maiwald, Volker, Oberst, Jürgen, Richter, Martin, Reynders, Martin, Schanz, Lars, Schmidt-Tedd, Bernhard, Wüst, Sabine, Detsis, Emmanouil, Masson, Frederic, Oriol, Stephane, Girard, Nathalie, Worms, Jean-Claude, Ferraris, Simona, Tosi, Maria Cristina, Cesaretti, Giovanni, Piragino, Antonio, Andreussi, Tommaso, Misuri, Tommaso, Reissner, Alexander, Krejci, David, Kuijper, Jim C., Bergmann, Benedikt, Pospisil, Stanislav, Stekl, Ivan, Brandt, Tim, Koroteev, Anatoly S., Semenkin, Alexander V., Solodukhin, Alexander E., Popov, Garri A., Petrukovich, A., Funaki, Ikkoh, Tinslay, Tim, Nogueira Frutuoso Guimaraes, Lamartine, del Amo, Jose G., and Schmidt, Georg
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crewed spaceflight ,telepresence ,INPPS ,Mars (planet) ,TRIPLE ,electric thrusters ,Europa (moon) ,droplet radiator ,nuclear-electric propulsion ,transfer trajectories ,VaMEx - Published
- 2021
32. Mars-/Europa-INPPS Flagship Missions: High and Low Power Electric Thrusters, Orbits/Payloads and Co-Flying Satellites
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Jansen, Frank, Ehresmann, Manfred, Funke, Oliver, Grill, Julia, Grundmann, Jan Thimo, Herdrich, Georg, Hillebrandt, Martin, Maiwald, Volker, Oberst, Jürgen, Richter, Martin, Reynders, Martin, Schanz, Lars, Schmidt-Tedd, Bernhard, Damme, Friedrich, Bergmann, Benedikt, Pospisil, Stanislav, Stekl, Ivan, Brandt, Tim, Detsis, Emmanouil, Masson, Frederic, Oriol, Stephane, Worms, Jean-Claude, Ferraris, Simona, Tosi, Maria Cristina, Tinslay, Tim, Funaki, Ikkoh, Nogueira Frutuoso Guimaraes, Lamartine, Koroteev, Anatoly S., Semenkin, Alexander V., Solodukhin, Alexander E., Popov, Garri A., Petrukovich, A., and Kuijper, Jim C.
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crewed spaceflight ,telepresence ,INPPS ,Mars (planet) ,TRIPLE ,electric thrusters ,droplet radiator ,Europa (moon) ,nuclear-electric propulsion ,VaMEx ,interplanetary transfer orbit - Published
- 2021
33. Non-Human and Human Transport to Mars: by Mars- plus Europa-INPPS Flagship Missions including High Mass Science Payload
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Jansen, Frank, Funke, Oliver, Grundmann, Jan Thimo, Hillebrandt, Martin, Maiwald, Volker, Oberst, Jürgen, Richter, Martin, Reynders, Martin, Schanz, Lars, Schmidt-Tedd, Bernhard, Damme, Friedrich, Bergmann, Benedikt, Pospisil, Stanislav, Stekl, Ivan, Detsis, Emmanouil, Masson, Frederic, Oriol, Stephane, Worms, Jean-Claude, Tinslay, Tim, Funaki, Ikkoh, Nogueira Frutuoso Guimaraes, Lamartine, Koroteev, Anatoly S., Semenkin, Alexander V., Solodukhin, Alexander E., and Kuijper, Jim C.
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crewed spaceflight ,telepresence ,INPPS ,Mars (planet) ,FAIM/GRIPS ,TRIPLE ,Europa (moon) ,VaMEx - Published
- 2021
34. Magnetic Properties of Asteroid (162173) Ryugu
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Hercik, David, Auster, Hans-Ulrich, Constantinescu, Dragos, Blum, Jürgen, Fornaçon, Karl-Heinz, Fujimoto, Masaki, Gebauer, Kathrin, Grundmann, Jan-Thimo, Güttler, Carsten, Hillenmaier, Olaf, Ho, Tra-Mi, Hördt, Andreas, Krause, Christian, Kührt, Ekkehard, Lorda, Laurence, Matsuoka, Ayako, Motschmann, Uwe, Moussi-Soffys, Aurélie, Richter, Ingo, Sasaki, Kaname, Scholten, Frank, Stoll, Bernd, Weiss, Benjamin P, Wolff, Friederike, Glassmeier, Karl-Heinz, Hercik, David, Auster, Hans-Ulrich, Constantinescu, Dragos, Blum, Jürgen, Fornaçon, Karl-Heinz, Fujimoto, Masaki, Gebauer, Kathrin, Grundmann, Jan-Thimo, Güttler, Carsten, Hillenmaier, Olaf, Ho, Tra-Mi, Hördt, Andreas, Krause, Christian, Kührt, Ekkehard, Lorda, Laurence, Matsuoka, Ayako, Motschmann, Uwe, Moussi-Soffys, Aurélie, Richter, Ingo, Sasaki, Kaname, Scholten, Frank, Stoll, Bernd, Weiss, Benjamin P, Wolff, Friederike, and Glassmeier, Karl-Heinz
- Abstract
©2020. The Authors. Observations of the magnetization state of asteroids indicate diverse properties. Values between 1.9 × 10 -6Am2/kg (Eros) and 10-2 Am2/kg (Braille) have been reported. A more detailed understanding of asteroidal magnetic properties allows far-reaching conclusions of the magnetization mechanism as well as the strength of the magnetic field of the solar system regions the asteroid formed in. The Hayabusa2 mission with its lander Mobile Asteroid Surface Scout is equipped with a magnetometer experiment, MasMag. MasMag is a state-of-the-art three-axis fluxgate magnetometer, successfully operated also on Philae, the Rosetta mission lander. MasMag has enabled, after Eros for the second time ever, to determine the magnetic field of an asteroid during descent and on-surface operations. The new observations show that Ryugu, a low-albedo C-type asteroid, has no detectable global magnetization, and any local magnetization is either small (< 10−6 Am2/kg) or on very small (subcentimeter) scales. This implies, for example, that energetic solar wind particles could reach and alter the surface unimpeded by strong asteroidal magnetic fields, such as minimagnetospheres in case of the Moon.
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- 2021
35. This is what a MASCOT can do for you - at Apophis
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Lange, Caroline, Ho, Tra-Mi, Borella, Laura, Chand, Suditi, Grundmann, Jan Thimo, and Lichtenheldt, Roy
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(162173) Ryugu ,Hera ,Gossamer-1 ,Raumfahrt-Systemdynamik ,potentially hazardous asteroid ,MASCOT ,near-Earth asteroid ,Systementwicklung und Projektbüro ,(65803) Didymos ,Systemanalyse Raumsegment ,MicrOmega ,GoSolAr ,MASCOT2 ,MasCam ,(99942) Apophis ,Low Frequency Radar ,MasMag ,nanolander ,Avioniksysteme ,AIM ,MARA ,Mechanik und Thermalsysteme ,planetary radar ,AIDA ,Hayabusa2 - Abstract
In a similarly brief event some 10½ years before Apophis' fly-by on Friday, April 13th, 2029, the Mobile Asteroid Surface Scout, MASCOT, successfully completed its 17-hours mission on the ~km-sized C-type potentially hazardous asteroid (162173) Ryugu. Investigating the surface and its thermal properties, looking for a magnetic field, and imaging the stark landscapes of this dark rubble pile, it contributed valuable close-up information before the surface sampling by its mothership, HAYABUSA2. We outline the capabilities of the asteroid nanolanders MASCOT, MASCOT2, and the options for optimized MASCOT@Apophis designs in particular for small spacecraft rendezvous missions to Apophis.
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- 2020
36. Low-thrust: the fast & flexible path to Apophis
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Chand, Suditi, Ceriotti, Matteo, Grundmann, Jan Thimo, Kesseler, Lars, Moore, Iain, Vergaaij, Merel, and Viavattene, Giulia
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Gossamer-1 ,(99942) Apophis ,potentially hazardous asteroid ,Solar-electric propulsion ,near-Earth asteroid ,Systementwicklung und Projektbüro ,Mechanik und Thermalsysteme ,Systemanalyse Raumsegment ,GoSolAr ,low-thrust trajectories ,concurrent engineering - Abstract
By the time of Apophis' fly-by on Friday, April 13th, 2029, more satellites than have ever been launched since the beginning of the space age to this day will reach low Earth orbit (LEO). Almost all of them will be microsatellites of less than ~250 kg equipped with solar-electric propulsion (SEP). We propose the use of already created low-thrust trajectories to Apophis to help advance design trades in the early study phases of missions to Apophis. It appears that small spacecraft missions could benefit from solar-electric or sail propulsion.
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- 2020
37. Apophis and the Waves - The need for Frequency Coordination and Radio Amateur and University Community Support Before, During, After Close Approach
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Grundmann, Jan Thimo, Fexer, Sebastian, Laabs, M., and Plettemeier, Dirk
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amateur radio ,(99942) Apophis ,potentially hazardous asteroid ,frequency coordination ,citizen science ,Avioniksysteme ,near-Earth asteroid ,Systementwicklung und Projektbüro ,Mechanik und Thermalsysteme ,Systemanalyse Raumsegment ,planetary radar - Abstract
On Earth most definitely and likely also around the Moon, in the few days centred on Friday, April 13th, 2029, 21:45 UT, every informed and curious naked eye, lens, mirror and dish within the horizon will be aimed at (99942) Apophis for an once-in-a-1000 years opportunity of scientific observations. Most will watch or listen. Many will transmit. Some will get in the way of others. And a few will blast it with all they can - for the best of science. We intend to start the discussion to include the public in the unique observation of Apophis, in particular focusing on the radio amateur community and the need for world-wide coordination to avoid mutual interference.
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- 2020
38. INTERPLANETARY BY MARS-/EUROPA-INPPS FLAGSHIP & ORBITING SATELLITE
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Jansen, Frank, Funke, Oliver, Grundmann, Jan Thimo, Hillebrandt, Martin, Maiwald, Volker, Oberst, Jürgen, Richter, Martin, Schanz, Lars, Damme, Friedrich, Kühn, Daniel, Waldmann, Ch., Price, Colin, Bergmann, benedikt, Brandt, Tim, Pospisil, Stanislav, Stekl, Ivan, Detsis, Emmanouil, Granjon, Richard, Masson, Frederic, Muszynski, Micek, Worms, Jean-Claude, Ferraris, Simona, Tosi, Maria Cristina, Findlay, James AP, Tinslay, Tim, Funaki, Ikkoh, Guimarães, L.N.F., Koroteev, Anatoly S., Semenkin, Alexander V., Solodukhin, Alexander E., Popov, Garry, Petukhov, Viacheslav, and Kuijper, Jim C.
- Subjects
INPPS flagship ,UN NPS regulations and TIMEPIX - Published
- 2019
39. The MMX Rover: Performing in-situ Surface Investigations on Phobos
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Michel, Patrick, primary, Ulamec, Stephan, additional, Boettger, Ute, additional, Grott, Matthias, additional, Murdoch, Naomi, additional, Vernazza, Pierre, additional, Sunday, Cecily, additional, Zhang, Yun, additional, Valette, Rudy, additional, Castellani, Romain, additional, Biele, Jens, additional, Tardivel, Simon, additional, Groussin, Olivier, additional, Jorda, Laurent, additional, Knollenberg, Joerg, additional, Grundmann, Jan Thimo, additional, Arrat, Denis, additional, Pont, Gabriel, additional, Mary, Stéphane, additional, Grebenstein, Markus, additional, Miyamoto, Hirdy, additional, Nakamura, Tomoki, additional, Wada, Koji, additional, Yoshikawa, Kent, additional, and Kuramoto, Kiyoshi, additional
- Published
- 2021
- Full Text
- View/download PDF
40. Magnetic Properties of Asteroid (162173) Ryugu
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Hercik, David, primary, Auster, Hans‐Ulrich, additional, Constantinescu, Dragos, additional, Blum, Jürgen, additional, Fornaçon, Karl‐Heinz, additional, Fujimoto, Masaki, additional, Gebauer, Kathrin, additional, Grundmann, Jan‐Thimo, additional, Güttler, Carsten, additional, Hillenmaier, Olaf, additional, Ho, Tra‐Mi, additional, Hördt, Andreas, additional, Krause, Christian, additional, Kührt, Ekkehard, additional, Lorda, Laurence, additional, Matsuoka, Ayako, additional, Motschmann, Uwe, additional, Moussi‐Soffys, Aurélie, additional, Richter, Ingo, additional, Sasaki, Kaname, additional, Scholten, Frank, additional, Stoll, Bernd, additional, Weiss, Benjamin P., additional, Wolff, Friederike, additional, and Glassmeier, Karl‐Heinz, additional
- Published
- 2020
- Full Text
- View/download PDF
41. MASCOT operations on Ryugu - focus on some specific tasks
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Krause, Christian, Moussi-Soffys, Aurelie, Lorda, Laurence, Ho, Tra-Mi, Biele, Jens, Ulamec, Stephan, Lange, Caroline, Dudal, Clement, Cenac-Morthe, Celine, Granena, David, Canalias, Elisabet, Maibaum, Michael, Fantinati, Cinzia, Bibring, Jean-Pierre, Jaumann, Ralf, Glassmeier, Karl Heinz, Hercik, David, Grott, Matthias, Schmitz, Nicole, Wolff, Friederike, Kayal, Kagan, Grundmann, Jan Thimo, Sasaki, Kaname, Okada, Tatsuaki, Yoshimitsu, Tetsuo, Mimasu, Yuya, and Tsuda, Yuichi
- Subjects
Planetengeologie ,Lander Mascot ,Asterois ,Planetenphysik ,Planetare Sensorsysteme ,Systementwicklung und Projektbüro ,Operation ,Nutzerzentrum für Weltraumexperimente (MUSC) ,Hayabusa2 - Abstract
Hayabusa2 is an asteroid sample return mission operated by the Japanese space agency, JAXA. It was launched in December 2014. In July 2018, the spacecraft has reached the mission target after a 4-year-long cruise. The objective is a C-type primordial asteroid called Ryugu, in search of organic and hydrated minerals that might give essential clues for the solar system formation. The small lander MASCOT (Mobile Asteroid surface SCOuT) carried aboard Hayabusa2 landed on the surface on the 3rd of October 2018 for reliminary in-situ investigations while the probe is aiming to study Ryugu on a global scale and to return samples to Earth. MASCOT was jointly developed by the German Aerospace Centre (DLR) and the Centre National d'Etudes Spatiales (CNES). It is equipped with a sensor suite consisting of four fully-fledged instruments. DLR was responsible for developing the MASCOT lander and ground segment, and was in charge of planning and conducting lander joint operations from MUSC. CNES supplied the hyperspectral IR spectrometer (MicrOmega, IAS Paris), antennae and power system, provided a support to operations and was in charge of the flight dynamics aspects of the mission. The 17 hours of on-asteroid operations exceeded expectations and the overall landing and operations were a huge success. Indeed, the characteristics of the Ryugu asteroid such as the shape and the gravity were known only after arrival of Hayabusa2 in July 2018 and the operating ccontext was very constrained but did not provide from fulfilling the objectives. This paper is a complement to the overall paper on MASCOT landing and first results. It will focus on several operational tasks such as communication and power subsystems assessments as well as flight dynamics computations needed in real time and for postprocessing.
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- 2019
42. INPPS Flagship: 2020th and 2030th Mars Explorations
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Jansen, Frank, Bergmann, Benedikt, Brandt, Tim, Damme, Friedrich, Detsis, Emmanouil, Ferraris, Simona, Findlay, James AP, Funaki, Ikkoh, Funke, Oliver, Grundmann, Jan Thimo, Guimarães, L.N.F., Hillebrandt, Martin, Koroteev, Anatoly S., Kühn, Daniel, Kuijper, Jim C., Masson, Frederic, Maiwald, Volker, Oberst, J., Oriol, Stephane, Pospisil, Stanislav, Richter, Martin, Schanz, Lars, Semenkin, Alexander V., Solodukhin, Alexander S., Stekl, Ivan, Tinsley, Tim, Tosi, Cristina Maria, and Worms, Jean-Claude
- Subjects
Funktionsleichtbau ,Space and Nuclear Demonstrators 5) 2025 to 2030th: Mars-Earth-Mars-Earth-Jupiter/Europa missions and INPPS Flagship ,Controlling, Logistik ,Sub-Systems including Reactor ,3) DEMOCRITOS / MEGAHIT INPPS Flagship System ,Planetengeodäsie ,2) Non-human & Human High Power Space Transportation Hybrid Space Tug ,1) Mars-INPPS Flagship ,4) DEMOCRITOS Ground ,6) INPPS with science ,commercial and communication payloads - Abstract
The presentation summarizes INPPS (International Nuclear Power and Propulsion System) flagship non-human (2020th) and human (2030th) Mars exploration missions. The 2020th first flagship space flight is the complex, complete test mission for the second flagship towards Mars with humans (2030th). The most efficient approach is the completely tested first INPPS in the 2020th as the preparation of the second flagship with humans on board. The second INPPS (2030th) is also the regular space transportation tug Mars-Earth. International requests for human Mars space flight is realizable by rationales for pursuing two INPPS Mars missions in the proposed period: 1) successful finalization of the European-Russian DEMOCRITOS and MEGAHIT projects with their three concepts of space, ground and nuclear demonstrators for INPPS realization (2017), 2) successful ground based test of the Russian nuclear reactor with 1MWel plus the important thermal emission solution by droplet radiators (2018), 3) reactor space qualification by Russia until 2025 and 4) the perfect celestial Earth-Mars-Earth-Jupiter/Europa trajectory in 2026-2031 to carryout maximal INPPS space flight tests. Set of issues of INPPS space system and all subsystems became identified and studied during DEMOCRITOS. Consequently critical performance will be studied by parallel realizations of the ground and nuclear demonstrators (until 2025). The INPPS space demonstrator considers directly results of ground and nuclear demonstrator tests. Realization of the space demonstrator in form of the first space qualification of INPPS with all subsystems in the middle of the 2020th plus INPPS tests for about one to two years - first in high Earth orbit and later in nearby Earth space environment means a complete concepts driven approval for all INPPS technologies for non-human/human INPPS-Mars missions. Space subsystem results of MARS-INPPS design (with arrow wing shaped radiators) will be described. In dependence - from a cluster with worldwide selected electric thrusters - the MARS-INPPS payload mass is up to 18 tons. This very high payload mass allows to transport three different payloads at once - scientific, pure commercial and new media communication. The realization including tests is sketched: especially the need of non-human flagship Mars flight, the test towards Europa (including real time radiation monitoring) for maximal human Mars mission preparation for the second INPPS with humans to Mars. INPPS missions implicate Apollo and ISS comparable outcomes for science technologies, international dedication and in addition for space commercialization. Insofar - this MARS-INPPS presentation - convince high attendance of conference participants, commercial and new media investors.
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- 2019
43. Mars / Europa INPPS Flagship: All right for UN NPS Principles
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Jansen, Frank, Brandt, Tim, Grundmann, Jan Thimo, Koroteev, Anatoly S., Kuijper, Jim C., Lehnert, Christopher, Reynders, Martin, Schanz, Lars, Schmidt-Tedd, Bernhard, Semenkin, Alexander V., and Solodukhin, Alexander E.
- Subjects
Controlling, Logistik ,4) INPPS Flagship Commercialization and Communication Aspects ,1) UN Principles for NPS 2) EC DEMOCRITOS & MEGAHIT & DiPOP projects 3) INPPS Flagship: Human & Non-human High Power Space Transportation Hybrid Space Tug - Abstract
The presentation gives an overview of the current plans for the INPPS (International Nuclear Power and Propulsion System) Flagship design as well as related scenarios for utilization and puts these efforts in context with related legal and political challenges. In the last years (2017/2018) significant technological progress has been achieved as the nuclear reactor, radiator and propulsion subsystems of INPPS Flagship have successfully passed partial ground testing. Thus, the next step towards the INPPS goal of efficient and effective transport missions to Mars / Phobos and Jupiter / Europa has been taken. Hence, it is important to consider wider aspects for the overall mission implementation phase. Mission components such as the nuclear reactor as the power source for the propulsion system will have to comply with the 1992 UN principles relevant to the use of nuclear power sources (NPS) in outer space as well as scepticism at a time of low appetite for nuclear energy before implementation. Therefore in addition to an update on current technical state of art, this paper will look into the political questions related to the mission design, requirements of associated safety regulations and economic aspects for INPPS Flagship commercialization and international communication. The paper will show that the rationales for pursuing the implementation of this flagship mission are derived from a technological push but also from wider strategic aspects that benefit a variety of stakeholders and serve multiple goals. The interactive presentation will include videos related to INPPS Flagship, international interviews for Mars exploration mission by NPS, description of UN principles of NPS as well as commercialization and international communication aspects.
- Published
- 2019
44. Concept for a Gossamer solar power array using thin‑film photovoltaics
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Spröwitz, Tom, Banik, Udayan, Grundmann, Jan Thimo, Haack, Frederik, Hillebrandt, Martin, Martens, Hauke, Meyer, Sebastian, Reershemius, Siebo, Reininghaus, Nies, Sasaki, Kaname, Seefeldt, Patric, Sergeev, Oleg, Spietz, Peter, Sznajder, Maciej, Toth, Norbert, Vehse, Martin, Wippermann, Torben, Zander, Martin E., and Springer, Vienna
- Subjects
Funktionsleichtbau ,Solar Arrays ,mechanisms ,deployable structures ,Stadt- und Gebäudetechnologien ,deployment Systems ,flexible photovoltaic ,Mechanik und Thermalsysteme ,environmental testing ,Qualitätsmanagement - Abstract
The power demand for future satellite applications will continue to rise. Geostationary telecom-munication satellites currently approach a power level of up to 20 kW. Future spacecraft will provide yet more transponders and/or direct mobile-satellite services. Electric propulsion is in-creasingly used for station keeping, attitude control and GEO circularization. Interplanetary mis-sions already use kW-range electric propulsion. Space Tugs are studied for several fields. Suitable engines require 100 kW or more. The envisaged use of such engines and the operation of future GEO satellites lead to a renewed interest in large, deployable and ultra-lightweight power gen-erators in space. Within the GoSolAr (Gossamer Solar Array) activity, DLR develops a new photovoltaic array technology for power generation. It is based on the DLR Gossamer approach using lightweight, deployable CFRP booms and a polymer membrane covered with thin-film CIGS photovoltaics. The booms are arranged in a crossed configuration with a central deployment unit. The photovol-taic area is composed of one large square membrane with double folding using two-dimensional deployment. Even though the efficiency of thin-film photovoltaics is currently only about 1/3 of that of con-ventional photovoltaics, a membrane based array can already achieve better mass/power ratios. A 50 kW array requires an area of approximately 20 m x 20 m. In a first step, DLR develops a fully functional 5 m x 5 m demonstrator partially covered with thin-film photovoltaics, using the DLR small satellite platform S2TEP. Space compatible thin-film photovoltaics need to be select-ed and tested. They are integrated on standardized generator modules that will be assembled into a large, foldable and deployable membrane. A controlled deployment of structure and membrane, and a sufficiently stiff support structure for operation are key development topics. We present the conceptual design of the GoSolAr demonstrator, the main requirements, prelimi-nary technical budgets and the development strategy. An overview will be given on the selection and the maturity of the key technologies and subsystems, such as deployable membrane with in-tegrated photovoltaic generators; deployable CFRP booms including deployment mechanisms; photovoltaic cell selection and integration to generator units; the array harness concept as well as the electronics concept, for operation and photovoltaics characterization. Furthermore, an over-view of the first manufactured breadboard models and their testing will be presented, e.g. com-bined testing of booms and mechanically representative generator arrays to evaluate deployment and interface forces for the preliminary design.
- Published
- 2019
45. High Power Electric Propulsion: MARS plus EUROPA – Already Beyond 2025!
- Author
-
Jansen, Frank, Grundmann, Jan Thimo, Maiwald, Volker, Schanz, Lars, Masson, Frederic, Oriol, Stephane, Worms, Jean-Claude, Detsis, Emmanouil, Lassoudiere, Francois, Granjon, Richard, Tosi, Maria Cristina, Ferraris, Simona, Koroteev, Anatoly S., Semenkin, Alexander V., Solodukhin, Alexander E., Lovtsov, Alexander S., Kareevskij, Andrey V., Tinsley, Tim, Findlay, James A., Hodgson, Zara, Brandt, Tim, Pospisil, Stanisilav, Stekl, Ivan, Guimarães, L.N.F., Grunwald, Gerhard, Hillebrandt, Martin, Richter, Martin, Atanasois, D., Popov, Garri A., and Leiter, Hans
- Subjects
Funktionsleichtbau ,Controlling, Logistik ,High Power Space Transportation ,Systementwicklung und Projektbüro ,Systemanalyse Raumsegment - Abstract
It’s mid-term realization plus global strategic investments: the results of the European Russian DEMOCRITOS project (Horizon 2020) related to the MW class INPPS (International Nuclear Power and Propulsion System) flagship will be described. INPPS flagship includes high power electric thrusters cluster, supplied electric power by the nuclear reactor (successfully tested in Russia) and a solar power ring. Two INPPS versions were studied – the wide and arrow wing versions. Both versions have a futuristic design with standardized interfaces for several flagship subsystems. Especially the high payload mass of INPPS allows the transport of – for example – up to 12 t to JUPITER moon EUROPA and about 18 t to MARS – as a function of specific impulse of electric thrusters. INPPS flagship not only allows scientific, but especially commercial and communication payloads as well. This means industrial-scale production of space flight systems for robotic and human space exploration. International cooperation related to INPPS realization are necessary within an International High Power Space Transportation program to realize the DEMOCRITOS core, ground and space components until 2025. DEMOCRITOS project included partners from Europe, Russia and a Brazilian guest observer and received several inputs from NASA Cleveland and JAXA Tokyo.
- Published
- 2019
46. Flights are ten a sail - Re-use and commonality in the design and system engineering of small spacecraft solar sail missions with modular hardware for responsive and adaptive exploration
- Author
-
Grundmann, Jan Thimo, Bauer, Waldemar, Boden, Ralf, Ceriotti, Matteo, Chand, Suditi, Heiligers, M.J., Vergaaij, Merel, Viavattene, Giulia, and Wolff, Friederike
- Subjects
Responsive space ,Small spacecraft solar sail ,System engineering ,Small solar system body characterisation ,Multiple NEA rendezvous ,Small spacecraft asteroid lander - Abstract
The exploration of small solar system bodies started with fast fly-bys of opportunity on the sidelines of missions to the planets. The tiny new worlds seen turned out to be so intriguing and different from all else (and each other) that dedicated sample-return and in-situ analysis missions were developed and launched. Through these, highly efficient low-thrust propulsion expanded from commercial use into mainstream and flagship science missions, there in combination with gravity assists propulsion. In parallel, the growth of small spacecraft solutions accelerated in numbers as well as individual spacecraft capabilities. The on-going missions OSIRIS-REX (NASA) or HAYABUSA2 (JAXA) with its landers MINERVA-II and MASCOT, and the upcoming NEASCOUT mission are examples of this synergy of trends. The continuation of these and other related devlopments towards a propellant-less and highly efficient class of spacecraft for solar system exploration emerges in the form of small spacecraft solar sails designed for carefree handling and equipped with carried landers and application modules. These address the needs of all asteroid user communities - planetary science, planetary defence, and in-situ resource utilization - as well as other fields of solar system science and applications such as space weather warning and solar observations. Already the DLR-ESTEC GOSSAMER Roadmap for Solar Sailing initiated studies of missions uniquely feasible with solar sails such as Displaced L1 (DL1) space weather advance warning and monitoring and Solar Polar Orbiter (SPO) delivery, which demonstrate the capabilities of near-term solar sails to reach any kind of orbit in the inner solar system. This enables Multiple Near-Earth Asteroid (NEA) rendezvous missions (MNR), from Earth-coorbital to extremely inclined and even retrograde target orbits. For these mission types using separable payloads, design concepts can be derived from the separable Boom Sail Deployment Units characteristic of DLR GOSSAMER solar sail technology, nanolanders like MASCOT, or microlanders like the JAXA-DLR Jupiter Trojan Asteroid Lander for the OKEANOS mission which can shuttle from the sail to the targets visited and enable multiple NEA sample-return missions. These nanospacecraft scale components are an ideal match creating solar sails in micro-spacecraft format whose launch configurations are compatible with secondary payload platforms such as ESPA and ASAP. The DLR GOSSAMER solar sail technology builds on the experience gained in the development of deployable membrane structures leading up to the successful ground deployment test of a (20 m)2 solar sail at DLR Cologne in 1999 and in the 20 years since.
- Published
- 2019
47. From Idea to Flight - A Review of the MASCOT Development and a Comparison to Historical Fast-Paced Space Programs
- Author
-
Grimm, Christian, Grundmann, Jan Thimo, Hendrikse, Jeffrey, Lange, Caroline, Ziach, Christian, and Ho, Tra-Mi
- Subjects
Asteroid Lander ,MASCOT ,Land und Explorationstechnologie ,Skunk Works ,Systementwicklung und Projektbüro ,Concurrent AIV ,Faster Better Cheaper ,Hayabusa2 ,Satellite Manufacturing - Abstract
Now spanning a time frame of already 10 years, the plan to land a European Lander on an asteroid has finally been accomplished. The first idea was established around 2008 in the framework of the European Marco Polo Assessment, studying the possibility to collect a pristine sample of a Near-Earth Asteroid and returning it back to Earth. The lander named MASCOT (Mobile Asteroid Surface Scout) was proposed to be carried by the main spacecraft, to land on the surface and by the ability to relocate to investigate multiple surface locations in order to scout the best possible sampling site. After the discontinuation of the original study, MASCOT received an invitation from JAXA to join-in the Hayabusa2 mission, the direct follow-up of the first asteroid sampler Hayabusa. However, MASCOT was selected at a time (mid 2011) when its conceptual design and scientific payloads had not been fully defined; with the carrier spacecraft already in its critical design phase having most of its interfaces fixed; no heritage to use off-the-shelf bus equipment directly and only 3 years left until a proposed final delivery. The tight schedule, tightly defined envelope, and strict margins policy were challenges during its development at all levels. Nevertheless, Hayabusa2 and MASCOT were launched on December 3rd, 2014, and arrived at their destined target asteroid (162173) Ryugu on June 27, 2018. Finally, MASCOT was separated from its mother spacecraft and successfully landed on October 3rd, 2018, accomplishing the first ever landing of a European spacecraft on the surface of an asteroid. This paper provides a review of the performed MASCOT development process including its verification strategy from the first unit hardware test to the final check-out before launch. In addition, it also provides a historical comparison to former fast-paced programs in space.
- Published
- 2018
48. One size fits all? Customization of standard space systems engineering approaches for missions with and within DLR Institute of Space Systems
- Author
-
Lange, Caroline, Grundmann, Jan Thimo, Ho, Tra-Mi, Jahnke, Stephan Siegfried, Jetzschmann, Michael, Krömer, Olaf, Martelo Gomez, Antonio, Nohka, Falk, Scharringhausen, Marco, and Suhr, Birgit
- Subjects
space system design ,system engineering - Published
- 2018
49. Flights are ten a sail - Re-use and commonality in the design and system engineering of small spacecraft solar sail missions with modular hardware for responsive and adaptive exploration
- Author
-
Grundmann, Jan Thimo (author), Bauer, Waldemar (author), Boden, Ralf (author), Ceriotti, Matteo (author), Chand, Suditi (author), Heiligers, M.J. (author), Vergaaij, Merel (author), Viavattene, Giulia (author), Wolff, Friederike (author), Grundmann, Jan Thimo (author), Bauer, Waldemar (author), Boden, Ralf (author), Ceriotti, Matteo (author), Chand, Suditi (author), Heiligers, M.J. (author), Vergaaij, Merel (author), Viavattene, Giulia (author), and Wolff, Friederike (author)
- Abstract
The exploration of small solar system bodies started with fast fly-bys of opportunity on the sidelines of missions to the planets. The tiny new worlds seen turned out to be so intriguing and different from all else (and each other) that dedicated sample-return and in-situ analysis missions were developed and launched. Through these, highly efficient low-thrust propulsion expanded from commercial use into mainstream and flagship science missions, there in combination with gravity assists propulsion. In parallel, the growth of small spacecraft solutions accelerated in numbers as well as individual spacecraft capabilities. The on-going missions OSIRIS-REX (NASA) or HAYABUSA2 (JAXA) with its landers MINERVA-II and MASCOT, and the upcoming NEASCOUT mission are examples of this synergy of trends. The continuation of these and other related devlopments towards a propellant-less and highly efficient class of spacecraft for solar system exploration emerges in the form of small spacecraft solar sails designed for carefree handling and equipped with carried landers and application modules. These address the needs of all asteroid user communities - planetary science, planetary defence, and in-situ resource utilization - as well as other fields of solar system science and applications such as space weather warning and solar observations. Already the DLR-ESTEC GOSSAMER Roadmap for Solar Sailing initiated studies of missions uniquely feasible with solar sails such as Displaced L1 (DL1) space weather advance warning and monitoring and Solar Polar Orbiter (SPO) delivery, which demonstrate the capabilities of near-term solar sails to reach any kind of orbit in the inner solar system. This enables Multiple Near-Earth Asteroid (NEA) rendezvous missions (MNR), from Earth-coorbital to extremely inclined and even retrograde target orbits. For these mission types using separable payloads, design concepts can be derived from the separable Boom Sail Deployment Units characteris, Astrodynamics & Space Missions
- Published
- 2019
50. Membrane Deployment Technology Development at DLR for Solar Sails and Large-Scale Photovoltaics
- Author
-
Tom Sproewitz, Seefeldt, Patric, Spietz, Peter, Grundmann, Jan Thimo, Jahnke, Rico, Mikulz, Eugen, Reershemius, Siebo, Renger, Thomas, Sasaki, Kaname, Sznajder, Maciej, and Toth, Norbert
- Subjects
huge solar arrays ,Gossamer-1 ,gossamer structures ,Membrane-based structures ,controlled deployment ,Systementwicklung und Projektbüro ,Technology qualification ,solar sail ,Mechanik und Thermalsysteme ,GoSolAr ,test facilities - Abstract
Following the highly successful flight of the first interplanetary solar sail, JAXA's IKAROS, with missions in the pipeline such as NASA's NEASCOUT nanospacecraft solar sail and JAXA's Solar Power Sail solar-electric propelled mission to a Jupiter Trojan asteroid, and on the back-ground of the ever increasing power demand of GEO satellites now including all-electric spacecraft, there is renewed interest in large lightweight structures in space. Among these, deployable membrane or 'gossamer' structures can provide very large functional area units for innovative space applications which can be stowed into the limited volumes of launch vehicle fairings as well as secondary payload launch slots, depending on the scale of the mission. Large area structures such as solar sails or high-power photovoltaic generators require a technology that allows their controlled and thereby safe deployment. Before employing such technology for a dedicated science or commercial mission, it is necessary, to demonstrate its reliability, i.e., TRL 6 or higher. A reliable technology that enables controlled deployment was developed in the GOSSAMER-1 solar sail deployment demonstrator project of the German Aerospace Center, DLR, including verification of its functionality with various laboratory tests to qualify the hardware for a first demonstration in low Earth orbit. We provide an overview of the GOSSAMER-1 hardware development and qualification campaign. The design is based on a crossed boom configuration with triangular sail segments. Employing engineering models, all aspects of the deployment were tested under ambient environment. Several components were also subjected to environmental qualification testing. An innovative stowing and deployment strategy for a controlled deployment and the required mechanisms are described. The tests conducted provide insight into the deployment process and allow a mechanical characterization of this process, in particular the measurement of the deployment forces. The stowing and deployment strategy was verified by tests with an engineering qualification model of one out of four GOSSAMER-1 deployment units. According to a test-as-you-fly approach the tests included vibration tests, venting, thermal-vacuum tests and ambient deployment. In these tests the deployment strategy proved to be suitable for a controlled deployment of gossamer spacecraft, and deployment on system level was demonstrated to be robust and controllable. The GOSSAMER-1 solar sail membranes were also equipped with small thin-film photovoltaic arrays intended to supply the core spacecraft. In our follow-on project GOSOLAR, the focus is now entirely on deployment systems for huge thin-film photovoltaic arrays. Based on the GOSSAMER-1 experience, deployment technology and qualification strategies, new technologies for the integration of thin-film photovoltaics are being developed and qualified for a first in-orbit technology demonstration within five years. Main objective is the further development of deployment technology for a 25 m² gossamer solar power generator and a flexible photovoltaic membrane. GOSOLAR enables a wider range of deployment concepts beyond solar sail optimized methods. It uses the S²TEP bus system developed at the Institute of Space Systems as part of the DLR satellite roadmap.
- Published
- 2018
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