Dokument-ID Dokumenttyp Verfasser/Autoren Herausgeber Haupttitel Abstract Auflage Verlagsort Verlag Erscheinungsjahr Seitenzahl Schriftenreihe Titel Schriftenreihe Bandzahl ISBN Quelle der Hochschulschrift Konferenzname Bemerkung Quelle:Titel Quelle:Jahrgang Quelle:Heftnummer Quelle:Erste Seite Quelle:Letzte Seite URN DOI Zugriffsart Link Abteilungen OPUS4-323 Konferenzveröffentlichung Dachwald, Bernd, dachwald@fh-aachen.de; Mikucki, Jill A., ; Tulaczyk, Slawek, ; Digel, Ilya, digel@fh-aachen.de; Feldmann, Marco, feldmann@fh-aachen.de; Espe, Clemens, c.espe@fh-aachen.de; Plescher, Engelbert, plescher@fh-aachen.de; Xu, Changsheng, IceMole - a maneuverable probe for clean in-situ analysis and sampling of subsurface ice and subglacial aquatic ecosystems : extended abstract / SCAR Open Science Conference 2012, Session 29: Advancing Clean Technologies for Exploration of Glacial Aquatic Ecosystems The "IceMole" is a novel maneuverable subsurface ice probe for clean in-situ analysis and sampling of subsurface ice and subglacial water/brine. It is developed and build at FH Aachen University of Applied Sciences' Astronautical Laboratory. A first prototype was successfully tested on the Swiss Morteratsch glacier in 2010. Clean sampling is achieved with a hollow ice screw (as it is used in mountaineering) at the tip of the probe. Maneuverability is achieved with a differentially heated melting head. Funded by the German Space Agency (DLR), a consortium led by FH Aachen currently develops a much more advanced IceMole probe, which includes a sophisticated system for obstacle avoidance, target detection, and navigation in the ice. We intend to use this probe for taking clean samples of subglacial brine at the Blood Falls (McMurdo Dry Valleys, East Antarctica) for chemical and microbiological analysis. In our conference contribution, we 1) describe the IceMole design, 2) report the results of the field tests of the first prototype on the Morteratsch glacier, 3) discuss the probe's potential for the clean in-situ analysis and sampling of subsurface ice and subglacial liquids, and 4) outline the way ahead in the development of this technology. 2012 Fachbereich Luft- und Raumfahrttechnik OPUS4-325 Konferenzveröffentlichung Dachwald, Bernd, dachwald@fh-aachen.de; Xu, Changsheng, ; Feldmann, Marco, feldmann@fh-aachen.de; Plescher, Engelbert, plescher@fh-aachen.de; Digel, Ilya, digel@fh-aachen.de; Artmann, Gerhard, artmann@fh-aachen.de Development and testing of a subsurface probe for detection of life in deep ice : [abstract] We present the novel concept of a combined drilling and melting probe for subsurface ice research. This probe, named "IceMole", is currently developed, built, and tested at the FH Aachen University of Applied Sciences' Astronautical Laboratory. Here, we describe its first prototype design and report the results of its field tests on the Swiss Morteratsch glacier. Although the IceMole design is currently adapted to terrestrial glaciers and ice shields, it may later be modified for the subsurface in-situ investigation of extraterrestrial ice, e.g., on Mars, Europa, and Enceladus. If life exists on those bodies, it may be present in the ice (as life can also be found in the deep ice of Earth). 2011 Fachbereich Medizintechnik und Technomathematik OPUS4-328 Konferenzveröffentlichung Digel, Ilya, digel@fh-aachen.de; Leimena, W., ; Dachwald, Bernd, dachwald@fh-aachen.de; Linder, Peter, linder@fh-aachen.de; Porst, Dariusz, porst@fh-aachen.de; Kayser, Peter, kayser@fh-aachen.de; Funke, O., ; Temiz Artmann, Aysegül, a.artmann@fh-aachen.de; Artmann, Gerhard, artmann@fh-aachen.de In-situ biological decontamination of an ice melting probe : [abstract] The objective of our study was to investigate the efficacy of different in-situ decontamination protocols in the conditions of thermo-mechanical ice-melting. 2010 Fachbereich Medizintechnik und Technomathematik OPUS4-333 Konferenzveröffentlichung Digel, Ilya, digel@fh-aachen.de; Dachwald, Bernd, dachwald@fh-aachen.de; Artmann, Gerhard, artmann@fh-aachen.de; Linder, Peter, linder@fh-aachen.de; Funke, O., A concept of a probe for particle analysis and life detection in icy environments A melting probe equipped with autofluorescence-based detection system combined with a light scattering unit, and, optionally, with a microarray chip would be ideally suited to probe icy environments like Europa's ice layer as well as the polar ice layers of Earth and Mars for recent and extinct live. 2009 Fachbereich Medizintechnik und Technomathematik OPUS4-1912 Wissenschaftlicher Artikel Blome, Hans-Joachim, blome@fh-aachen.de; Seboldt, Wolfgang, ; Dachwald, Bernd, dachwald@fh-aachen.de; Richter, Lutz, Proposal for an integrated European Space Exploration Study San Diego, Calif. Univelt 2004 XI, 432 S. : Ill., graph. Darst. Space Debris and Space Traffic Management Symposium 2004 : proceedings of the International Academy of Astronautics Space Debris and Space Traffic Management Symposium, held in conjunction with the 55th International Astronautical Congress (IAC), October 4 - 8, 2004, Vancouver, British Columbia, Canada / ed. by Joerg Bendisch 0-87703-523-7 Proceedings IAC-2004-IAA, 3.6.1.06; Space Debris and Space Traffic Management Symposium <2004, Vancouver, British Columbia> ; International Academy of Astronautics Fachbereich Luft- und Raumfahrttechnik OPUS4-3505 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Seboldt, W., ; Loeb, H. W, ; Schartner, K.-H., Main Belt Asteroid Sample Return Mission Using Solar Electric Propulsion 2008 10 Acta Astronautica. 63 (2008), H. 1-4 0094-5765 International Astronautical Federation Congress <58, 2007, Hyderabad> ; International Astronautical Congress <58, 2007, Hyderabad> ; IAC-07-A3.5.07 91 101 campus http://dx.doi.org/10.1016/j.actaastro.2007.12.023 Fachbereich Luft- und Raumfahrttechnik OPUS4-3507 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Ohndorf, A., 1st ACT Global Trajectory Optimisation Competition : Results found at DLR 2007 10 Acta Astronautica. 61 (2007), H. 9 0094-5765 Global Trajectory Optimization ; Results of the First Competition Organised by the Advanced Concept Team (ACT) of the European Space Agency (ESA) 742 752 campus http://dx.doi.org/10.1016/j.actaastro.2007.03.011 Fachbereich Luft- und Raumfahrttechnik OPUS4-3509 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Seboldt, W., ; Richter, L., Multiple rendezvous and sample return missions to near-Earth objects using solar sailcraft / Dachwald, B. ; Seboldt, W. ; Richter, L. 2006 8 Acta Astronautica. 59 (2006), H. 8-11 0094-5765 International Conference on Low Cost Planetary Missions <5, 2003, Noordwijk> ; Selected Proceedings 768 776 campus http://dx.doi.org/10.1016/j.actaastro.2005.07.061 Fachbereich Luft- und Raumfahrttechnik OPUS4-3510 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Seboldt, W., Multiple Near-Earth Asteroid Rendezvous and Sample Return Using First Generation Solar Sailcraft 2005 11 Acta Astronautica. 57 (2005), H. 11 0094-5765 864 875 campus http://dx.doi.org/10.1016/j.actaastro.2005.04.012 Fachbereich Luft- und Raumfahrttechnik OPUS4-3511 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de Optimization of very-low-thrust trajectories using evolutionary neurocontrol 2005 10 Acta Astronautica. 57 (2005), H. 2-8 0094-5765 175 185 campus http://dx.doi.org/10.1016/j.actaastro.2005.03.004 Fachbereich Luft- und Raumfahrttechnik OPUS4-3525 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; McDonald, Malcolm, ; McInnes, Colin R., ; Mengali, Giovanni, Impact of Optical Degradation on Solar Sail Mission Performance 2007 9 Journal of Spacecraft and Rockets. 44 (2007), H. 4 0022-4650 2. ISSN: 1533-6794 740 749 campus http://dx.doi.org/10.2514/1.21432 Fachbereich Luft- und Raumfahrttechnik OPUS4-3526 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Wi, Bong, Solar Sail Kinetic Energy Impactor Trajectory Optimization for an Asteroid-Deflection Mission 2007 9 Journal of Spacecraft and Rockets. 44 (2007), H. 4 0022-4650 2. ISSN: 1533-6794 755 764 campus http://dx.doi.org/10.2514/1.22586 Fachbereich Luft- und Raumfahrttechnik OPUS4-3527 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de Minimum Transfer Times for Nonperfectly Reflecting Solar Sailcraft 2004 2 Journal of Spacecraft and Rockets. 41 (2004), H. 4 0022-4650 2. ISSN: 1533-6794 693 695 campus http://arc.aiaa.org/doi/pdf/10.2514/1.6279 Fachbereich Luft- und Raumfahrttechnik OPUS4-3528 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Mengali, Giovanni, ; Quarta, Alessandrao A., ; Macdonald, Malcolm, Parametric Model and Optimal Control of Solar Sails with Optical Degradation 2006 8 Journal of guidance, control, and dynamics. 29 (2006), H. 5 0162-3192 2. ISSN: 0731-5090 1170 1178 campus http://arc.aiaa.org/doi/pdf/10.2514/1.20313 Fachbereich Luft- und Raumfahrttechnik OPUS4-3530 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de Optimal Solar Sail Trajectories for Missions to the Outer Solar System 2005 6 Journal of guidance, control, and dynamics. 28 (2005), H. 6 0162-3192 2. ISSN: 0162-3192. - 3. ISSN: 0731-5090 1187 1193 campus http://arc.aiaa.org/doi/pdf/10.2514/6.2004-5406 Fachbereich Luft- und Raumfahrttechnik OPUS4-3531 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de Optimization of Interplanetary Solar Sailcraft Trajectories Using Evolutionary Neurocontrol 2004 6 Journal of guidance, control, and dynamics. 27 (2004), H. 1 0162-3192 2. ISSN: 0162-3192. - 3. ISSN: 0731-5090 66 72 campus http://arc.aiaa.org/doi/pdf/10.2514/1.9286 Fachbereich Luft- und Raumfahrttechnik OPUS4-3532 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de Entwicklung sicherer und wartbarer Software für den Eurofighter 1996 5 Soldat und Technik : Strategie und Technik, Sicherheit (1996) 0038-0989 663 668 Fachbereich Luft- und Raumfahrttechnik OPUS4-3584 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Kahle, Ralph, ; Wie, Bong, Solar Sailing Kinetic Energy Impactor (KEI) Mission Design Tradeoffs for Impacting and Deflecting Asteroid 99942 Apophis Reston, Va. American Institute of Aeronautics and Astronautics 2006 2 CD-ROMs. AIAA Guidance, Navigation, and Control Conference & Exhibit - AIAA Atmospheric Flight Mechanics Conference & Exhibit - AIAA Modeling and Simulation Technologies Conference & Exhibit - AIAA/AAS Astrodynamics Specialist Conference & Exhibit : [21 - 24 August 2006, Keystone, Colorado ; papers]. - (AIAA meeting papers on disc ; [11.]2006,19-20 ) 1-56347-802-1 American Institute of Aeronautics and Astronautics ; American Astronautical Society ; AIAA/AAS Astrodynamics Specialist Conference & Exhibit <2006, Keystone, Colo.> ; AIAA paper number: AIAA-2006-6178 1 20 weltweit http://www.spacesailing.net/paper/200608_Keystone_DachwaldKahleWie.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-3585 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Ohndorf, A., ; Wie, Bong, Solar Sail Trajectory Optimization for the Solar Polar Imager (SPI) Mission Reston, Va. American Institute of Aeronautics and Astronautics 2006 2 CD-ROMs. AIAA Guidance, Navigation, and Control Conference & Exhibit - AIAA Atmospheric Flight Mechanics Conference & Exhibit - AIAA Modeling and Simulation Technologies Conference & Exhibit - AIAA/AAS Astrodynamics Specialist Conference & Exhibit : [21 - 24 August 2006, Keystone, Colorado ; papers]. - (AIAA meeting papers on disc ; [11.]2006,19-20 ) 1-56347-802-1 American Institute of Aeronautics and Astronautics ; American Astronautical Society ; AIAA/AAS Astrodynamics Specialist Conference & Exhibit <2006, Keystone, Colo.> ; AIAA paper number: AIAA-2006-6177 weltweit http://www.spacesailing.net/paper/200608_Keystone_DachwaldOhndorfWie.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-3586 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Seboldt, Wolfgang, ; Macdonald, Malcolm, ; Mengali, Giovanni, ; Quatra, Alessandro A., ; McInnes, Colin R., ; Rios-Reyes, Leonel, ; Scheerers, Daniel J., ; Wie, Bong, ; Görlich, Marianne, ; Lura, Franz, ; Diedrich, Benjamin, ; Baturkin, Volodymyr, ; Coverstone, Victoria L., ; Leipold, Manfred, ; Garbe, Gregory P., Potential Solar Sail Degradation Effects on Trajectory and Attitude Control Reston, Va. American Institute of Aeronautics and Astronautics 2005 2 CD-ROMs AIAA Guidance, Navigation and Control Conference and Exhibit - AIAA Modeling and Simulation Technologies Conference and Exhibit - AIAA Atmospheric Flight Mechanics Conference and Exhibit : [San Francisco, California, 15 - 18 August 2005 ; papers]. - (AIAA meeting papers on disc ; [10.]2005,16-17) 1-56347-765-3 American Institute of Aeronautics and Astronautics ; AIAA Guidance, Navigation, and Control Conference and Exhibit <2005, San Francisco, Calif.> ; AIAA paper number: AIAA-2006-6172 Link "https://arc.aiaa.org/doi/book/10.2514/MGNC05" am 15.07.2022 nachgetragen Behr weltweit http://www.spacesailing.net/paper/200508_SanFrancisco_Dachwald+.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-3587 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Seboldt, W., ; Richter, L., Multiple Rendezvous and Sample Return Missions to Near-Earth Asteroids Using Solar Sailcraft Noordwijk ESA 2003 XVII, 545 S. : Ill., graph. Darst. Proceedings of the Fifth IAA International Conference on Low Cost Planetary Missions : 24 - 26 September 2003, ESTEC, Noordwijk, the Netherlands / [comp. by R. A. Harris] 92-9092-853-0 International Conference on Low Cost Planetary Missions <5, 2003, Noordwijk> ; International Academy of Astronautics ; European Space Research and Technology Centre 351 358 weltweit http://www.spacesailing.net/paper/200309_Noordwijk_DachwaldSeboldtRichter.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-3588 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Wie, Bong, Solar Sail Trajectory Optimization for Intercepting, Impacting, and Deflecting Near-Earth Asteroids Reston, Va. American Institute of Aeronautics and Astronautics 2005 2 CD-ROMs AIAA Guidance, Navigation and Control Conference and Exhibit - AIAA Modeling and Simulation Technologies Conference and Exhibit - AIAA Atmospheric Flight Mechanics Conference and Exhibit : [San Francisco, California, 15 - 18 August 2005 ; papers]. - (AIAA meeting papers on disc ; [10.]2005,16-17) 1-56347-765-3 American Institute of Aeronautics and Astronautics ; AIAA Guidance, Navigation, and Control Conference and Exhibit <2005, San Francisco, Calif.> ; AIAA paper number: AIAA-2006-6176 weltweit http://www.spacesailing.net/paper/200508_SanFrancisco_DachwaldWie.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-3589 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de Interplanetary Mission Analysis for Non-Perfectly Reflecting Solar Sailcraft Using Evolutionary Neurocontrol San Diego, Calif. Univelt 2004 XXIV S., S. 870-1741. : Ill., graph. Darst. Astrodynamics 2003 : proceedings of the AAS/AIAA Astrodynamics Conference held August 3 - 7, 2003, Big Sky, Montana / ed. by Jean de Lafontaine. - Pt. 2. - (Advances in the astronautical sciences ; 116,2) 0-87703-509-1 Astrodynamics Conference <2003, Big Sky, Mont.> ; American Institute of Aeronautics and Astronautics ; AAS-03-579 1247 1262 weltweit http://www.spacesailing.net/paper/200308_BigSky_Dachwald.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-3590 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de Verwendung eines neuronalen Reglers und evolutionärer Algorithmen zur Berechnung optimaler interplanetarer Sonnenseglerbahnen Bonn 2003 XLIV, 841 S. : zahlr. Ill., graph. Darst. Deutscher Luft- und Raumfahrtkongress 2003 : München, 17. bis 20. November 2003, Motto: 100 Jahre Motorflug - 112 Jahre Menschenflug: Visionen gestalten Zukunft / Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V. (DGLR). [Red.: Peter Brandt (verantwortlich)]. - Bd. 1. - (Jahrbuch ... der Deutschen Gesellschaft für Luft- und Raumfahrt) Deutscher Luft- und Raumfahrt-Kongreß <2003, München> ; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth ; DGLR-2002-089 211 218 weltweit http://www.spacesailing.net/paper/200209_Stuttgart_Dachwald.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-3591 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de Low-Thrust Trajectory Optimization and Interplanetary Mission Analysis Using Evolutionary Neurocontrol Bonn 2004 XXVI S., S. 785 - 1595 : zahlr. Ill., graph. Darst Deutscher Luft- und Raumfahrtkongress 2004 : Dresden, 20. bis 23. September 2004, Motto: Luft- und Raumfahrt - Brücke für eine wissensbasierte Gesellschaft / Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V. (DGLR). [Red.: Peter Brandt (verantwortlich)]. - Bd. 2. - (Jahrbuch ... der Deutschen Gesellschaft für Luft- und Raumfahrt) Deutscher Luft- und Raumfahrt-Kongress <2004, Dresden> ; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth ; DGLR-2004-116 917 926 weltweit http://www.spacesailing.net/paper/200409_Dresden_Dachwald.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-3592 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de Evolutionary Neurocontrol: A Smart Method for Global Optimization of Low-Thrust Trajectories Reston, Va. American Inst. of Aeronautics and Astronautics 2004 2 CD-ROMs 22nd AIAA Applied Aerodynamics Conference and Exhibit - AIAA/AAS Astrodynamics Specialist Conference and Exhibit - AIAA Guidance, Navigation, and Control Conference and Exhibit - AIAA Modeling and Simulation Technologies Conference and Exhibit - AIAA Atmospheric Flight Mechanics Conference and Exhibit : 16 - 19 August 2004, Providence, Rhode Island / American Institute of Aeronautics and Astronautics. - (AIAA meeting papers on disc ; 2004,14-15) American Institute of Aeronautics and Astronautics ; AIAA/AAS Astrodynamics Specialist Conference and Exhibit <2004, Providence, RI> ; AIAA paper number: AIAA-2004-5405 weltweit http://www.spacesailing.net/paper/200408_Providence_Dachwald_ENC.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-3573 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Carnelli, I., ; Vasile, M., Low-Thrust Gravity Assist Trajectory Optimization Using Evolutionary Neurocontrollers / I. Carnelli ; B. Dachwald ; M. Vasile ... San Diego, Calif. Univelt 2006 XXIII S.. S. 1860 - 2854. : Ill., graph. Darst. Astrodynamics 2005 : proceedings of the AAS/AIAA astrodynamics conference held August 7 - 11, 2005, South Lake Tahoe, California / ed. by Bobby G. Williams. - Pt. 3. - (Advances in the astronautical sciences ; 123,3) 0-87703-527-X Astrodynamics Conference <2005, South Lake Tahoe, Calif.> ; American Astronautical Society ; Number: AAS-05-374 1911 1928 Fachbereich Luft- und Raumfahrttechnik OPUS4-3574 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Leipold, M., ; Fichtner, H., Heliopause Explorer - A Sailcraft Mission to the Outer Boundaries of the Solar System / M. Leipold ; H. Fichtner ; B. Heber ... B. Dachwald ... Noordwijk ESA 2003 XVII, 545 S. : Ill., graph. Darst. Proceedings of the Fifth IAA International Conference on Low Cost Planetary Missions : 24 - 26 September 2003, ESTEC, Noordwijk, the Netherlands / [comp. by R. A. Harris] 92-9092-853-0 International Conference on Low Cost Planetary Missions <5, 2003, Noordwijk> ; International Academy of Astronautics ; European Space Research and Technology Centre 367 375 Fachbereich Luft- und Raumfahrttechnik OPUS4-3575 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Ohndorf, A., ; Seboldt, W., Optimierung der Lageregelung von Raumfahrzeugen mit Niedrigschubantrieb mittels evolutionärer neuronaler Regler / A. Ohndorf ; B. Dachwald ; W. Seboldt Bonn DGLR 2005 XIV, 1591 - 2264 S. : zahlr. Ill., graph. Darst. Deutscher Luft- und Raumfahrtkongress 2005 : Friedrichshafen, 26. bis 29. September 2005, Motto: Luft- und Raumfahrt - Grenzen überwinden, Horizonte erweitern / Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V. (DGLR). [Red.: Peter Brandt (verantwortlich)]. Bd. 3. - (Jahrbuch ... der Deutschen Gesellschaft für Luft- und Raumfahrt Deutscher Luft- und Raumfahrt-Kongress <2005, Friedrichshafen> ; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth ; Dokumentnr: DGLR-2005-224 1971 1978 Fachbereich Luft- und Raumfahrttechnik OPUS4-3579 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Baturkin, Volodymyr, ; Coverstone, Victoria L., ; Dietrich, Benjamin, ; Garbe, Gregory P., ; Görlich, Marianne, ; Leipold, Manfred, ; Lura, Franz, ; Macdonald, Malcolm, ; McInnes, Colin R., ; Mengali, Giovanni, ; Quatra, Alessandro A., ; Rios-Reyes, Leonel, ; Scheeres, Daniel J., ; Seboldt, Wolfgang, ; Wie, Bong, Potential Effects of Optical Solar Sail Degradation on Interplanetary Trajectory Design San Diego, Calif. Univelt 2006 XXIII S.. S. 1860 - 2854. : Ill., graph. Darst. Astrodynamics 2005 : proceedings of the AAS/AIAA astrodynamics conference held August 7 - 11, 2005, South Lake Tahoe, California / ed. by Bobby G. Williams. - Pt. 3. - (Advances in the astronautical sciences ; 123,3) 0-87703-527-X Astrodynamics Conference <2005, South Lake Tahoe, Calif.> ; American Astronautical Society ; Number: AAS-05-413 2569 2592 Fachbereich Luft- und Raumfahrttechnik OPUS4-3593 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de Optimal Solar Sail Trajectories for Missions to the Outer Solar System Reston, Va. American Inst. of Aeronautics and Astronautics 2004 2 CD-ROMs 22nd AIAA Applied Aerodynamics Conference and Exhibit - AIAA/AAS Astrodynamics Specialist Conference and Exhibit - AIAA Guidance, Navigation, and Control Conference and Exhibit - AIAA Modeling and Simulation Technologies Conference and Exhibit - AIAA Atmospheric Flight Mechanics Conference and Exhibit : 16 - 19 August 2004, Providence, Rhode Island / American Institute of Aeronautics and Astronautics. - (AIAA meeting papers on disc ; 2004,14-15) American Institute of Aeronautics and Astronautics ; AIAA/AAS Astrodynamics Specialist Conference and Exhibit <2004, Providence, RI> ; AIAA paper number: AIAA-2004-5406 weltweit http://www.spacesailing.net/paper/200408_Providence_Dachwald_Sail.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-3594 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Seboldt, W., Optimization of Interplanetary Rendezvous Trajectories for Solar Sailcraft Using a Neurocontroller Reston, Va. American Institute of Aeronautics and Astronautics 2002 S. 657-1310 A collection of technical papers / AIAA Astrodynamics Specialist Conference : Monterey, California, 5 - 8 August 2002. - Vol. 2 1-56347-549-9 Astrodynamics Specialist Conference <2002, Monterey, Calif.> American Institute of Aeronautics and Astronautics ; AIAA paper number: AIAA-2002-4989 1263 1270 weltweit http://www.spacesailing.net/paper/200208_Monterey_DachwaldSeboldt.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-3563 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Ohndorf, A., ; Gill, E., Optimization of low-thrust Earth-Moon transfers using evolutionary neurocontrol / Ohndorf, A. ; Dachwald, B. ; Gill, E. 2009 6 IEEE Congress on Evolutionary Computation, 2009. CEC '09. 978-1-4244-2958-5 358 364 campus http://dx.doi.org/10.1109/CEC.2009.4982969 Fachbereich Luft- und Raumfahrttechnik OPUS4-3564 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Mengali, Giovanni, ; Quarta, Alessandro A., ; Circi, Christian, Refined Solar Sail Force Model with Mission Application / Giovanni Mengali ; Alessandro A. Quarta , Christian Circi ; Bernd Dachwald 2007 8 Journal of Guidance, Control, and Dynamics. 30 (2007), H. 2 0162-3192 2. ISBN: 0731-5090 512 520 campus http://dx.doi.org/10.2514/1.24779 Fachbereich Luft- und Raumfahrttechnik OPUS4-3565 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; MacDonald, Malcolm, ; McInnes, Colin R., Heliocentric Solar Sail Orbit Transfers with Locally Optimal Control Laws / Malcolm Macdonald ; Colin McInnes ; Bernd Dachwald 2007 3 Journal of Spacecraft and Rockets. 44 (2007), H. 1 0022-4650 273 276 campus http://dx.doi.org/10.2514/1.17297 Fachbereich Luft- und Raumfahrttechnik OPUS4-3566 Wissenschaftlicher Artikel Leipold, M., ; Fichtner, H., ; Heber, B., ; Groepper, P., ; Lascar, S., ; Burger, F., ; Eiden, M., ; Niederstadt, T., ; Sickinger, C., ; Herbeck, L., ; Dachwald, Bernd, dachwald@fh-aachen.de; Seboldt, W., Heliopause Explorer - A Sailcraft Mission to the Outer Boundaries of the Solar System 2006 10 Acta Astronautica. 59 (2006), H. 8-11 0094-5765 International Conference on Low Cost Planetary Missions <5, 2003, Noordwijk> ; Selected Proceedings 786 796 campus http://dx.doi.org/10.1016/j.actaastro.2005.07.024 Fachbereich Luft- und Raumfahrttechnik OPUS4-3567 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Seboldt, W., Solar Sails for Near- and Medium-Term Scientific Deep Space Missions / W. Sebolt ; B. Dachwald Milano SP Lab, Politecnico di Milano 2005 getr. Zählung . Ill. In-space propulsion : edited book of proceedings of the 10-IWCP, the 10th International Workshop on Combustion and Propulsion held in Lerici, La Spezia, Italy, 21-25 September 2003 / [ed.: Luigi T. DeLuca] Paper 31 ; International workshop on combustion and propulsion <10, 2003, Lerici> Fachbereich Luft- und Raumfahrttechnik OPUS4-3568 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Seboldt, W., Solar Sails — Propellantless Propulsion for Near- and Medium-Term Deep-Space Missions / W. Seboldt ; B. Dachwald Reston, Va. AIAA 2008 460 S. Advanced Propulsion Systems and Technologies, Today to 2020 / Claudio Bruno (ed.) ... - (Progress in Astronautics and Aeronautics Series ; 223) 978-1-56347-929-8 ISBN 10: 1-56347-929-X ; American Institute of Aeronautics and Astronautics Fachbereich Luft- und Raumfahrttechnik OPUS4-3569 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Carnelli, I., ; Vasile, M., Optimizing low-thrust gravity assist interplanetary trajectories using evolutionary neurocontrollers / I. Carnelli ; B. Dachwald ; M. Vasile Piscataway, NJ IEEE Service Center 2007 XXVIII S., S. 3879 - 4328, 9 S. : Ill., graph. Dar IEEE Congress on Evolutionary Computation, 2007 : CEC 2007 ; 25 - 28 September 2007, Singapore 978-1-424-41339-3 ISBN 10: 1-424-41339-7 ; IEEE Congress on Evolutionary Computation <2007, Singapore> ; Institute of Electrical and Electronics Engineers ; Nebent: CEC 2007 ; Parallel als Online-Ausg. erschienen 965 972 campus http://dx.doi.org/10.1109/CEC.2007.4424574 Fachbereich Luft- und Raumfahrttechnik OPUS4-3570 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Carnelli, I., ; Vasile, M., Evolutionary Neurocontrol as a Novel Method for Low-Thrust Gravity Assist Trajectory Optimization / I. Carnelli ; B. Dachwald ; M. Vasile Tokyo JSASS 2006 XX, 1684, XIII S. : Ill., graph. Darst. Proceedings of the Twenty-Fifth International Symposium on Space Technology and Science (Selected papers) : Kanazawa, [June 4 through June 11, 2006, at Kanazawa-shi Kanko Kaikan in Kanazawa city] / [Japan Society for Aeronautical and Space Sciences. Kohtaro Matsumoto [ed.-in-chief] 4-99005-002-9 International Symposium on Space Technology and Science <25, 2006, Kanazawa> ; ISTS 2006-d-46 569 574 Fachbereich Luft- und Raumfahrttechnik OPUS4-3571 Wissenschaftlicher Artikel Dittus, H., ; Turyshev, S. G., ; Dachwald, Bernd, dachwald@fh-aachen.de; Blome, Hans-Joachim, blome@fh-aachen.de A Mission to Explore the Pioneer Anomaly Noordwijk ESA Publ. Div. 2005 X, 427 S : Ill., graph. Darst. Proceedings of the 39th ESLAB Symposium "Trends in Space Science and Cosmic Vision 2020" : 19 - 21 April 2005, ESTEC, Noordwijk, the Netherlands / European Space Agency. [Comp. by: F. Favata ...] . - (ESA SP ; 588) 9290928999 ISBN der CD-ROM-Ausg.: 9290928999 ; Symposium Trends in Space Science and Cosmic Vision 2020 <2005, Noordwijk> ; ESLAB symposium <39,2005, Noordwijk> ; European Space Laboratory ; Report Number: LA-UR-05-4907 ; The Pioneer Explorer Collaboration 3 10 weltweit http://arxiv.org/abs/gr-qc/0506139v1 Fachbereich Luft- und Raumfahrttechnik OPUS4-3572 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Turyshev, Slava G., ; Dittus, H., ; Shao, M. [u.a.], Fundamental Physics with the Laser Astrometric Test Of Relativity / S.G. Turyshev ; H. Dittus ; M. Shao ... B.Dachwald ... Noordwijk ESA Publ. Div. 2005 X, 427 S : Ill., graph. Darst. Proceedings of the 39th ESLAB Symposium "Trends in Space Science and Cosmic Vision 2020" : 19 - 21 April 2005, ESTEC, Noordwijk, the Netherlands / European Space Agency. [Comp. by: F. Favata ...] . - (ESA SP ; 588) 9290928999 ISBN der CD-ROM-Ausg.: 9290928999 ; Symposium Trends in Space Science and Cosmic Vision 2020 <2005, Noordwijk> ; ESLAB symposium <39, 2005, Noordwijk> ; European Space Laboratory 8 11 weltweit http://arxiv.org/abs/gr-qc/0506104v3 Fachbereich Luft- und Raumfahrttechnik OPUS4-3536 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Seboldt, W., ; Lämmerzahl, W., Solar Sail Propulsion: An Enabling Technology for Fundamental Physics Missions Berlin [u.a.] Springer 2008 XIX, 639 S. : Ill., graph. Darst. Lasers, Clocks and Drag Free Control : Exploration of Relativistic Gravity in Space / by Hansjörg Dittus ..., eds. - ( Astrophysics and Space Science Library ; 349) 978-3-540-34376-9 379 398 Fachbereich Luft- und Raumfahrttechnik OPUS4-3904 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Carnelli, Ian, ; Vasile, Massimiliano, Evolutionary Neurocontrol: A Novel Method for Low-Thrust Gravity-Assist Trajectory Optimization / Carnelli, Ian ; Dachwald, Bernd ; Vasile, Massimiliano Reston, Va. AIAA 2009 9 Journal of guidance control and dynamics. 32 (2009), H. 2 0731-5090 616 625 bezahl http://dx.doi.org/10.2514/1.32633 Fachbereich Luft- und Raumfahrttechnik OPUS4-3905 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Ball, Andrew J., ; Ulamec, Stephan, ; Price, Michael E., A small mission for in situ exploration of a primitive binary near-Earth asteroid / Ball, Andrew J. ; Ulamec, Stephan ; Dachwald, Bernd ; Price, Michael E. ; [u.a.] Amsterdam Elsevier 2009 7 Advances in Space Research. 43 (2009), H. 2 0273-1177 317 324 campus http://dx.doi.org/10.1016/j.asr.2008.04.015 Fachbereich Luft- und Raumfahrttechnik OPUS4-4153 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Seboldt, Wolfgang, Solar sailcraft of the first generation technology development / Seboldt, Wolfgang ; Dachwald, Bernd 2003 54th International Astronautical Congress of the International Astronautical Federation, the International Academy of Astronautics, and the International Institute of Space Law 29 September - 3 October 2003, Bremen, Germany IAC-03-S.03 weltweit http://pdf.aiaa.org/preview/CDReadyMIAF03_860/PVIAC_03_S_6_03.pdf [abstract] Fachbereich Luft- und Raumfahrttechnik OPUS4-4147 Wissenschaftlicher Artikel Scholz, A., ; Ley, Wilfried, ley@fh-aachen.de; Dachwald, Bernd, dachwald@fh-aachen.de; Miau, J. J., ; Juang, J. C., Flight results of the COMPASS-1 picosatellite mission 2010 9 Acta Astronautica. 67 (2010), H. 9-10 0094-5765 1289 1298 campus http://dx.doi.org/10.1016/j.actaastro.2010.06.040 Fachbereich Luft- und Raumfahrttechnik OPUS4-4151 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Seboldt, Wolfgang, Solar sailcraft of the first generation mission applications to near-earth asteroids 2003 54th International Astronautical Congress of the International Astronautical Federation, the International Academy of Astronautics, and the International Institute of Space Law 29 September - 3 October 2003, Bremen, Germany IAC-03-Q.5.06 weltweit http://pdf.aiaa.org/preview/CDReadyMIAF03_860/PVIAC_03_Q_5_06.pdf [abstract] Fachbereich Luft- und Raumfahrttechnik OPUS4-4152 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Tsinas, L., A combined neural and genetic learning algorithm / Tsinas, L. ; Dachwald, B. Orlando, Fl 1994 4 Proceedings of the First IEEE Conference on Evolutionary Computation, 1994. IEEE World Congress on Computational Intelligence. 0-7803-1899-4 770 774 campus http://dx.doi.org/10.1109/ICEC.1994.349968 Fachbereich Luft- und Raumfahrttechnik OPUS4-4439 Wissenschaftlicher Artikel Scholz, Christina, ; Romagnoli, Daniele, ; Dachwald, Bernd, dachwald@fh-aachen.de; Theil, Stephan, Performance analysis of an attitude control system for solar sails using sliding masses Amsterdam Elsevier 2011 13 Advances in Space Research 48 11 1822 1835 campus http://dx.doi.org/10.1016/j.asr.2011.05.032 Fachbereich Luft- und Raumfahrttechnik OPUS4-4443 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Wurm, Patrick, Mission analysis and performance comparison for an Advanced Solar Photon Thruster Amsterdam Elsevier 2011 10 Advances in Space Research 48 11 1858 1868 campus http://dx.doi.org/10.1016/j.asr.2011.01.030 Fachbereich Luft- und Raumfahrttechnik OPUS4-4448 Wissenschaftlicher Artikel Maiwald, Volker, ; Dachwald, Bernd, dachwald@fh-aachen.de Mission Design for a Multiple-Rendezvous Mission to Jupiter's Trojans 2010 COSPAR 2010 ; 38th COSPAR Scientific Assembly. Held 18-25 July 2010 in Bremen, Germany [Abstract] 3 Fachbereich Luft- und Raumfahrttechnik OPUS4-4538 Wissenschaftlicher Artikel Leimena, W., ; Artmann, Gerhard, artmann@fh-aachen.de; Dachwald, Bernd, dachwald@fh-aachen.de; Temiz Artmann, Aysegül, a.artmann@fh-aachen.de; Gossmann, Matthias, ; Digel, Ilya, digel@fh-aachen.de Feasibility of an in-situ microbial decontamination of an ice-melting probe 2010 5 Eurasian Chemico-Technological Journal. 12 (2010), H. 2 1562-3920 145 150 Fachbereich Medizintechnik und Technomathematik OPUS4-4930 Wissenschaftlicher Artikel Digel, Ilya, digel@fh-aachen.de; Dachwald, Bernd, dachwald@fh-aachen.de; Artmann, Gerhard, artmann@fh-aachen.de; Linder, Peter, linder@fh-aachen.de; Funke, O., A concept of a probe for particle analysis and life detection in icy environments 2009 23 International workshop "Europa lander: science goals and experiments", Space Research Institute (IKI), Moscow, Russia 9-13 February 2009 1 24 weltweit http://www.iki.rssi.ru/conf/2009elw/presentations/presentations_pdf/session7/digel_ELW.pdf Fachbereich Medizintechnik und Technomathematik OPUS4-4939 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Schmidt, Tanja D., ; Seboldt, Wolfgang, ; Auweter-Kurtz, , Flight Opportunities from Mars to Earth for Piloted Missions Using Continuous Thrust Propulsion / Schmidt, Tanja D. ; Dachwald, Bernd ; Seboldt, Wolfgang ; Auweter-Kurtz, Monika - 2003 8 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 20-23 July 2003, Huntsville, Alabama ; AIAA 2003-4573 1 9 campus http://arc.aiaa.org/doi/pdf/10.2514/6.2003-4573 Fachbereich Luft- und Raumfahrttechnik OPUS4-5510 Teil eines Buches Dachwald, Bernd, dachwald@fh-aachen.de; Ulamec, Stephan, ; Biele, Jens, Clean in situ subsurface exploration of icy environments in the solar system "To assess the habitability of the icy environments in the solar system, for example, on Mars, Europa, and Enceladus, the scientific analysis of material embedded in or underneath their ice layers is very important. We consider self-steering robotic ice melting probes to be the best method to cleanly access these environments, that is, in compliance with planetary protection standards. The required technologies are currently developed and tested." Dordrecht Springer 2013 30 Habitability of other planets and satellites. - (Cellular origin, life in extreme habitats and astrobiology ; 28) 978-94-007-6545-0 (Druckausgabe) 367 397 bezahl DOI:10.1007/978-94-007-6546-7_20 Fachbereich Luft- und Raumfahrttechnik OPUS4-6129 Wissenschaftlicher Artikel Krämer, Stefan, ; Daab, Dominique Jonas, ; Müller, Brigitte, ; Wagner, Tobias, ; Baader, Fabian, ; Hessel, Joana, ; Gdalewitsch, Georg, ; Plescher, Engelbert, plescher@fh-aachen.de; Dachwald, Bernd, dachwald@fh-aachen.de; Wahle, Michael, wahle@fh-aachen.de; Gierse, Andreas, ; Vetter, Rudolf, ; Pfützenreuter, Lysan, Development and flight-testing of a system to isolate vibrations for microgravity experiments on sounding rockets 2013 7 21st ESA Symposium on Rocket and Balloon Research 1 8 https://www.researchgate.net/publication/258449040_DEVELOPMENT_AND_FLIGHT-TESTING_OF_A_SYSTEM_TO_ISOLATE_VIBRATIONS_FOR_MICROGRAVITY_EXPERIMENTS_ON_SOUNDING_ROCKETS Fachbereich Luft- und Raumfahrttechnik OPUS4-6374 Teil eines Buches Dachwald, Bernd, dachwald@fh-aachen.de; Boehnhardt, Herrmann, ; 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, Gossamer roadmap technology reference study for a multiple NEO Rendezvous Mission A technology reference study for a multiple near-Earth object (NEO) rendezvous mission with solar sailcraft is currently carried out by the authors of this paper. The investigated mission builds on previous concepts, but adopts a strong micro-spacecraft philosophy based on the DLR/ESA Gossamer technology. The main scientific objective of the mission is to explore the diversity of NEOs. After direct interplanetary insertion, the solar sailcraft should—within less than 10 years—rendezvous three NEOs that are not only scientifically interesting, but also from the point of human spaceight and planetary defense. In this paper, the objectives of the study are outlined and a preliminary potential mission profile is presented. Berlin [u.a.] Springer 2014 15 Advances in solar sailing 978-3-642-34906-5 (Print) ; 978-3-642-34907-2 (E-Book) 211 226 bezahl http://dx.doi.org/10.1007/978-3-642-34907-2_15 Fachbereich Luft- und Raumfahrttechnik OPUS4-6375 Teil eines Buches McInnes, Colin R., ; Bothmer, Volker, ; Dachwald, Bernd, dachwald@fh-aachen.de; Geppert, Ulrich R. M. E., ; Heiligers, Jeannette, ; Hilgers, Alan, ; Johnson, Les, ; Macdonald, Malcolm, ; Reinhard, Ruedeger, ; Seboldt, Wolfgang, ; Spietz, Peter, Gossamer roadmap technology reference study for a Sub-L1 Space Weather Mission A technology reference study for a displaced Lagrange point space weather mission is presented. The mission builds on previous concepts, but adopts a strong micro-spacecraft philosophy to deliver a low mass platform and payload which can be accommodated on the DLR/ESA Gossamer-3 technology demonstration mission. A direct escape from Geostationary Transfer Orbit is assumed with the sail deployed after the escape burn. The use of a miniaturized, low mass platform and payload then allows the Gossamer-3 solar sail to potentially double the warning time of space weather events. The mission profile and mass budgets will be presented to achieve these ambitious goals. Berlin [u.a.] Springer 2014 15 Advances in solar sailing 978-3-642-34906-5 (Print) ; 978-3-642-34907-2 (E-Book) 227 242 bezahl http://dx.doi.org/10.1007/978-3-642-34907-2_16<7A> Fachbereich Luft- und Raumfahrttechnik OPUS4-6376 Teil eines Buches Macdonald, Malcolm, ; McGrath, C., ; Appourchaux, T., ; Dachwald, Bernd, dachwald@fh-aachen.de; Finsterle, W., ; Gizon, L., ; Liewer, P. C., ; McInnes, Colin R., ; Mengali, G., ; Seboldt, W., ; Sekii, T., ; Solanki, S. K., ; Velli, M., ; Wimmer-Schweingruber, R. F., ; Spietz, Peter, ; Reinhard, Ruedeger, Macdonald, Malcolm Gossamer roadmap technology reference study for a solar polar mission A technology reference study for a solar polar mission is presented. The study uses novel analytical methods to quantify the mission design space including the required sail performance to achieve a given solar polar observation angle within a given timeframe and thus to derive mass allocations for the remaining spacecraft sub-systems, that is excluding the solar sail sub-system. A parametric, bottom-up, system mass budget analysis is then used to establish the required sail technology to deliver a range of science payloads, and to establish where such payloads can be delivered to within a given timeframe. It is found that a solar polar mission requires a solar sail of side-length 100-125 m to deliver a 'sufficient value' minimum science payload, and that a 2.5 μm sail film substrate is typically required, however the design is much less sensitive to the boom specific mass. Berlin, Heidelberg Springer 2014 14 Advances in solar sailing 978-3-642-34906-5 243 257 10.1007/978-3-642-34907-2_17 weltweit https://doi.org/10.1007/978-3-642-34907-2_17 Fachbereich Luft- und Raumfahrttechnik OPUS4-6618 Konferenzveröffentlichung Konstantinidis, K., ; Dachwald, Bernd, dachwald@fh-aachen.de; Ohndorf, A., ; Dykta, P., ; Voigt, K., ; Förstner, R., Enceladus explorer (ENEX): A lander mission to probe subglacial water pockets on Saturn's moon enceladus for life Red Hook, NY Curran 2013 10 64th International Astronautical Congress 2013 (IAC 2013) : Beijing, China, 23 - 27 September 2013. (Proceedings of the International Astronautical Congress, IAC ; 2) 978-1-62993-909-4 1340 1350 Fachbereich Luft- und Raumfahrttechnik OPUS4-6619 Konferenzveröffentlichung Dachwald, Bernd, dachwald@fh-aachen.de; Feldmann, Marco, feldmann@fh-aachen.de; Espe, Clemens, c.espe@fh-aachen.de; Plescher, Engelbert, plescher@fh-aachen.de; Konstantinidis, K., ; Forstner, R., Enceladus explorer - A maneuverable subsurface probe for autonomous navigation through deep ice Red Hook, NY Curran 2012 10 63rd International Astronautical Congress 2012, IAC 2012; Naples; Italy; 1 October 2012 through 5 October 2012. (Proceedings of the International Astronautical Congress, IAC ; 3) 978-1-62276-979-7 1756 1766 Fachbereich Luft- und Raumfahrttechnik OPUS4-6684 Wissenschaftlicher Artikel Konstantinidis, Konstantinos, ; Flores Martinez, Claudio, ; Dachwald, Bernd, dachwald@fh-aachen.de; Ohndorf, Andreas, ; Dykta, Paul, ; Bowitz, Pascal, ; Rudolph, Martin, ; Digel, Ilya, digel@fh-aachen.de; Kowalski, Julia, kowalski@fh-aachen.de; Voigt, Konstantin, ; Förstner, Roger, A lander mission to probe subglacial water on Saturn's moon enceladus for life Amsterdam Elsevier 2015 26 Acta astronautica Vol. 106 63 89 campus http://dx.doi.org/10.1016/j.actaastro.2014.09.012 Fachbereich Luft- und Raumfahrttechnik OPUS4-6790 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Mikucki, Jill, ; Tulaczyk, Slawek, ; Digel, Ilya, digel@fh-aachen.de; Espe, Clemens, c.espe@fh-aachen.de; Feldmann, Marco, feldmann@fh-aachen.de; Francke, Gero, ; Kowalski, Julia, kowalski@fh-aachen.de; Xu, Changsheng, IceMole : A maneuverable probe for clean in situ analysis and sampling of subsurface ice and subglacial aquatic ecosystems There is significant interest in sampling subglacial environments for geobiological studies, but they are difficult to access. Existing ice-drilling technologies make it cumbersome to maintain microbiologically clean access for sample acquisition and environmental stewardship of potentially fragile subglacial aquatic ecosystems. The IceMole is a maneuverable subsurface ice probe for clean in situ analysis and sampling of glacial ice and subglacial materials. The design is based on the novel concept of combining melting and mechanical propulsion. It can change melting direction by differential heating of the melting head and optional side-wall heaters. The first two prototypes were successfully tested between 2010 and 2012 on glaciers in Switzerland and Iceland. They demonstrated downward, horizontal and upward melting, as well as curve driving and dirt layer penetration. A more advanced probe is currently under development as part of the Enceladus Explorer (EnEx) project. It offers systems for obstacle avoidance, target detection, and navigation in ice. For the EnEx-IceMole, we will pay particular attention to clean protocols for the sampling of subglacial materials for biogeochemical analysis. We plan to use this probe for clean access into a unique subglacial aquatic environment at Blood Falls, Antarctica, with return of a subglacial brine sample. Cambridge Cambridge University Press 2014 8 Annals of Glaciology 55 65 14 22 10.3189/2014AoG65A004 bezahl https://doi.org/10.3189/2014AoG65A004 Fachbereich Luft- und Raumfahrttechnik OPUS4-7435 Konferenzveröffentlichung Peloni, Alessandro, ; Ceriotti, Matteo, ; Dachwald, Bernd, dachwald@fh-aachen.de Solar-Sailing Trajectory Design for Close-up NEA Observations Mission 2015 21 S. 4th IAA Planetary Defense Conference - PDC 2015, 13-17 April 2015, Frascati, Roma, Italy IAA-PDC-15-P-19 weltweit https://www.researchgate.net/publication/274387241_Solar-Sailing_Trajectory_Design_for_Close-up_NEA_Observations_Mission/a> Fachbereich Luft- und Raumfahrttechnik OPUS4-7584 Wissenschaftlicher Artikel Kowalski, Julia, kowalski@fh-aachen.de; Linder, Peter, linder@fh-aachen.de; Zierke, S., ; Wulfen, B. van, ; Clemens, J., ; Konstantinidis, K., ; Ameres, G., ; Hoffmann, R., ; Mikucki, J., ; Tulaczyk, S., ; Funke, O., ; Blandfort, D., ; Espe, Clemens, c.espe@fh-aachen.de; Feldmann, Marco, feldmann@fh-aachen.de; Francke, Gero, francke@fh-aachen.de; Hiecker, S., ; Plescher, Engelbert, plescher@fh-aachen.de; Schöngarth, Sarah, schoengarth@fh-aachen.de; Dachwald, Bernd, dachwald@fh-aachen.de; Digel, Ilya, digel@fh-aachen.de; Artmann, Gerhard, artmann@fh-aachen.de; Eliseev, D., ; Heinen, D., ; Scholz, F., ; Wiebusch, C., ; Macht, S., ; Bestmann, U., ; Reineking, T., ; Zetzsche, C., ; Schill, K., ; Förstner, R., ; Niedermeier, H., ; Szumski, A., ; Eissfeller, B., ; Naumann, U., ; Helbing, K., Navigation technology for exploration of glacier ice with maneuverable melting probes The Saturnian moon Enceladus with its extensive water bodies underneath a thick ice sheet cover is a potential candidate for extraterrestrial life. Direct exploration of such extraterrestrial aquatic ecosystems requires advanced access and sampling technologies with a high level of autonomy. A new technological approach has been developed as part of the collaborative research project Enceladus Explorer (EnEx). The concept is based upon a minimally invasive melting probe called the IceMole. The force-regulated, heater-controlled IceMole is able to travel along a curved trajectory as well as upwards. Hence, it allows maneuvers which may be necessary for obstacle avoidance or target selection. Maneuverability, however, necessitates a sophisticated on-board navigation system capable of autonomous operations. The development of such a navigational system has been the focal part of the EnEx project. The original IceMole has been further developed to include relative positioning based on in-ice attitude determination, acoustic positioning, ultrasonic obstacle and target detection integrated through a high-level sensor fusion. This paper describes the EnEx technology and discusses implications for an actual extraterrestrial mission concept. Amsterdam Elsevier 2016 17 Cold Regions Science and Technology 123 53 70 10.1016/j.coldregions.2015.11.006 bezahl https://doi.org/10.1016/j.coldregions.2015.11.006 Fachbereich Medizintechnik und Technomathematik OPUS4-7585 Wissenschaftlicher Artikel Grundmann, Jan Thimo, ; Dachwald, Bernd, dachwald@fh-aachen.de; Grimm, Christian D., ; Kahle, Ralph, ; Koch, Aaron Dexter, ; Krause, Christian, ; Lange, Caroline, ; Quantius, Dominik, ; Ulamec, Stephan, Spacecraft for Hypervelocity Impact Research - An Overview of Capabilities, Constraints and the Challenges of Getting There Amsterdam Elsevier 2015 7 Procedia Engineering Vol. 103 Proceedings of the 2015 Hypervelocity Impact Symposium (HVIS 2015) 151 158 10.1016/j.proeng.2015.04.021 Fachbereich Luft- und Raumfahrttechnik OPUS4-7586 Konferenzveröffentlichung Grundmann, Jan Thimo, ; Bauer, Waldemar, ; Biele, Jens, ; Cordero, Frederico, ; Dachwald, Bernd, dachwald@fh-aachen.de; Koncz, Alexander, ; Krause, Christian, ; Mikschl, Tobias, ; Montenegro, Sergio, ; Quantius, Dominik, ; Ruffer, Michael, ; Sasaki, Kaname, ; Schmitz, Nicole, ; Seefeldt, Patric, ; Tóth, Norbert, ; Wejmo, Elisabet, From Sail to Soil - Getting Sailcraft Out of the Harbour on a Visit to One of Earth's Nearest Neighbours 2015 20 S. 4th IAA Planetary Denfense Conference - PDC 2015, 13-17 April 2015, Frascati, Roma, Italy weltweit http://iaaweb.org/iaa/Scientific Activity/conf/pdc2015/IAA-PDC-15-04-17.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-7587 Konferenzveröffentlichung Pirovano, Laura, ; Seefeldt, Patric, ; Dachwald, Bernd, dachwald@fh-aachen.de; Noomen, Ron, Attitude and Orbital Dynamics Modeling for an Uncontrolled Solar-Sail Experiment in Low-Earth Orbit 2015 15 S. 25th International Symposium on Spaceflight Dynamics, 2015, Munich, Germany http://issfd.org/2015/files/downloads/papers/079_Pirovano.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-7609 Konferenzveröffentlichung Peloni, A., ; Ceriotti, M., ; Dachwald, Bernd, dachwald@fh-aachen.de Preliminary trajectory design of a multiple NEO rendezvous mission through solar sailing Red Hook, NY Curran 2015 14 Proceedings of the International Astronautical Congress, IAC, Vol. 8, 2014 978-1-63439-986-9 65th International Astronautical Congress 2014: Our World Needs Space, IAC 2014; Toronto; Canada; 29 September 2014 through 3 October 2014 5352 5366 Fachbereich Luft- und Raumfahrttechnik OPUS4-7943 Konferenzveröffentlichung Konstantinidis, K., ; Kowalski, Julia, kowalski@fh-aachen.de; Martinez, C. F., ; Dachwald, Bernd, dachwald@fh-aachen.de; Ewerhart, D., ; Förstner, R., Some necessary technologies for in-situ astrobiology on enceladus 2015 18 Proceedings of the International Astronautical Congress 978-151081893-4 6th International Astronautical Congress 2015: Space - The Gateway for Mankind's Future, IAC 2015; Jerusalem; Israel; 12 October 2015 through 16 October 2015 1354 1372 Fachbereich Luft- und Raumfahrttechnik OPUS4-8287 Konferenzveröffentlichung Grundmann, Jan Thimo, ; Meß, Jan-Gerd, ; Biele, Jens, ; Seefeldt, Patric, ; Dachwald, Bernd, dachwald@fh-aachen.de; Spietz, Peter, ; Grimm, Christian D., ; Spröwitz, Tom, ; Lange, Caroline, ; Ulamec, Stephan, Small spacecraft in small solar system body applications 2017 19 IEEE Aerospace Conference 2017, Big Sky, Montana, USA 978-1-5090-1613-6 Article No 7943626 1 20 10.1109/AERO.2017.7943626 campus https://doi.org/10.1109/AERO.2017.7943626 Fachbereich Luft- und Raumfahrttechnik OPUS4-8288 Wissenschaftlicher Artikel Peloni, Alessandro, ; Dachwald, Bernd, dachwald@fh-aachen.de; Ceriotti, Matteo, Multiple near-earth asteroid rendezvous mission: Solar-sailing options Amsterdam Elsevier 2017 Advances in Space Research In Press, Corrected Proof 10.1016/j.asr.2017.10.017 bezahl https://doi.org/10.1016/j.asr.2017.10.017 Fachbereich Luft- und Raumfahrttechnik OPUS4-10743 Teil eines Buches Dachwald, Bernd, dachwald@fh-aachen.de; Ulamec, Stephan, ; Kowalski, Julia, ; Boxberg, Marc S., ; Baader, Fabian, fabian.baader@fh-aachen.de; Biele, Jens, ; Kömle, Norbert, Badescu, Viorel; Zacny, Kris; Bar-Cohen, Yoseph Ice melting probes The exploration of icy environments in the solar system, such as the poles of Mars and the icy moons (a.k.a. ocean worlds), is a key aspect for understanding their astrobiological potential as well as for extraterrestrial resource inspection. On these worlds, ice melting probes are considered to be well suited for the robotic clean execution of such missions. In this chapter, we describe ice melting probes and their applications, the physics of ice melting and how the melting behavior can be modeled and simulated numerically, the challenges for ice melting, and the required key technologies to deal with those challenges. We also give an overview of existing ice melting probes and report some results and lessons learned from laboratory and field tests. Cham Springer 2023 41 Handbook of Space Resources 978-3-030-97912-6 (Print) 955 996 10.1007/978-3-030-97913-3_29 campus https://doi.org/10.1007/978-3-030-97913-3_29 Fachbereich Luft- und Raumfahrttechnik OPUS4-10890 misc Feldmann, Marco, ; Francke, Gero, ; Espe, Clemes, c.espe@fh-aachen.de; Chen, Qian, ; Baader, Fabian, fabian.baader@alumni.fh-aachen.de; Boxberg, Marc S., ; Sustrate, Anna-Marie, ; Kowalski, Julia, ; Dachwald, Bernd, dachwald@fh-aachen.de Performance data of an ice-melting probe from field tests in two different ice environments This dataset was acquired at field tests of the steerable ice-melting probe "EnEx-IceMole" (Dachwald et al., 2014). A field test in summer 2014 was used to test the melting probe's system, before the probe was shipped to Antarctica, where, in international cooperation with the MIDGE project, the objective of a sampling mission in the southern hemisphere summer 2014/2015 was to return a clean englacial sample from the subglacial brine reservoir supplying the Blood Falls at Taylor Glacier (Badgeley et al., 2017, German et al., 2021). The standardized log-files generated by the IceMole during melting operation include more than 100 operational parameters, housekeeping information, and error states, which are reported to the base station in intervals of 4 s. Occasional packet loss in data transmission resulted in a sparse number of increased sampling intervals, which where compensated for by linear interpolation during post processing. The presented dataset is based on a subset of this data: The penetration distance is calculated based on the ice screw drive encoder signal, providing the rate of rotation, and the screw's thread pitch. The melting speed is calculated from the same data, assuming the rate of rotation to be constant over one sampling interval. The contact force is calculated from the longitudinal screw force, which es measured by strain gauges. The used heating power is calculated from binary states of all heating elements, which can only be either switched on or off. Temperatures are measured at each heating element and averaged for three zones (melting head, side-wall heaters and back-plate heaters). 2022 Forschungsdaten zu "Field-test performance of an ice-melting probe in a terrestrial analogue environment" (https://opus.bibliothek.fh-aachen.de/opus4/frontdoor/index/index/docId/10889) 10.5281/zenodo.6094866 weltweit https://doi.org/10.5281/zenodo.6094866 Fachbereich Luft- und Raumfahrttechnik OPUS4-10889 Wissenschaftlicher Artikel Baader, Fabian, fabian.baader@alumni.fh-aachen.de; Boxberg, Marc S., ; Chen, Qian, ; Förstner, Roger, ; Kowalski, Julia, ; Dachwald, Bernd, dachwald@fh-aachen.de Field-test performance of an ice-melting probe in a terrestrial analogue environment Melting probes are a proven tool for the exploration of thick ice layers and clean sampling of subglacial water on Earth. Their compact size and ease of operation also make them a key technology for the future exploration of icy moons in our Solar System, most prominently Europa and Enceladus. For both mission planning and hardware engineering, metrics such as efficiency and expected performance in terms of achievable speed, power requirements, and necessary heating power have to be known. Theoretical studies aim at describing thermal losses on the one hand, while laboratory experiments and field tests allow an empirical investigation of the true performance on the other hand. To investigate the practical value of a performance model for the operational performance in extraterrestrial environments, we first contrast measured data from terrestrial field tests on temperate and polythermal glaciers with results from basic heat loss models and a melt trajectory model. For this purpose, we propose conventions for the determination of two different efficiencies that can be applied to both measured data and models. One definition of efficiency is related to the melting head only, while the other definition considers the melting probe as a whole. We also present methods to combine several sources of heat loss for probes with a circular cross-section, and to translate the geometry of probes with a non-circular cross-section to analyse them in the same way. The models were selected in a way that minimizes the need to make assumptions about unknown parameters of the probe or the ice environment. The results indicate that currently used models do not yet reliably reproduce the performance of a probe under realistic conditions. Melting velocities and efficiencies are constantly overestimated by 15 to 50 % in the models, but qualitatively agree with the field test data. Hence, losses are observed, that are not yet covered and quantified by the available loss models. We find that the deviation increases with decreasing ice temperature. We suspect that this mismatch is mainly due to the too restrictive idealization of the probe model and the fact that the probe was not operated in an efficiency-optimized manner during the field tests. With respect to space mission engineering, we find that performance and efficiency models must be used with caution in unknown ice environments, as various ice parameters have a significant effect on the melting process. Some of these are difficult to estimate from afar. Amsterdam Elsevier 2023 Artikel 115852 Icarus Forschungsdaten hierzu: "Performance data of an ice-melting probe from field tests in two different ice environments" (https://opus.bibliothek.fh-aachen.de/opus4/frontdoor/index/index/docId/10890) 409 10.1016/j.icarus.2023.115852 weltweit https://doi.org/10.1016/j.icarus.2023.115852 Fachbereich Luft- und Raumfahrttechnik OPUS4-8832 Konferenzveröffentlichung Baader, Fabian, fabian.baader@fh-aachen.de; Reiswich, M., ; Bartsch, M., ; Keller, D., ; Tiede, E., ; Keck, G., ; Demircian, A., ; Friedrich, M., ; Dachwald, Bernd, dachwald@fh-aachen.de; Schüller, K., ; Lehmann, R., ; Chojetzki, R., ; Durand, C., ; Rapp, L., ; Kowalski, Julia, kowalski@fh-aachen.de; Förstner, R., VIPER - Student research on extraterrestrical ice penetration technology Recent analysis of scientific data from Cassini and earth-based observations gave evidence for a global ocean under a surrounding solid ice shell on Saturn's moon Enceladus. Images of Enceladus' South Pole showed several fissures in the ice shell with plumes constantly exhausting frozen water particles, building up the E-Ring, one of the outer rings of Saturn. In this southern region of Enceladus, the ice shell is considered to be as thin as 2 km, about an order of magnitude thinner than on the rest of the moon. Under the ice shell, there is a global ocean consisting of liquid water. Scientists are discussing different approaches the possibilities of taking samples of water, i.e. by melting through the ice using a melting probe. FH Aachen UAS developed a prototype of maneuverable melting probe which can navigate through the ice that has already been tested successfully in a terrestrial environment. This means no atmosphere and or ambient pressure, low ice temperatures of around 100 to 150K (near the South Pole) and a very low gravity of 0,114 m/s^2 or 1100 μg. Two of these influencing measures are about to be investigated at FH Aachen UAS in 2017, low ice temperature and low ambient pressure below the triple point of water. Low gravity cannot be easily simulated inside a large experiment chamber, though. Numerical simulations of the melting process at RWTH Aachen however are showing a gravity dependence of melting behavior. Considering this aspect, VIPER provides a link between large-scale experimental simulations at FH Aachen UAS and numerical simulations at RWTH Aachen. To analyze the melting process, about 90 seconds of experiment time in reduced gravity and low ambient pressure is provided by the REXUS rocket. In this time frame, the melting speed and contact force between ice and probes are measured, as well as heating power and a two-dimensional array of ice temperatures. Additionally, visual and infrared cameras are used to observe the melting process. 2018 5 Proceedings of the 2nd Symposium on Space Educational Activities 1 6 weltweit Fachbereich Luft- und Raumfahrttechnik OPUS4-9089 Wissenschaftlicher Artikel Schael, S., ; Atanasyan, A., ; Berdugo, J., ; Bretz, T., ; Czupalla, Markus, czupalla@fh-aachen.de; Dachwald, Bernd, dachwald@fh-aachen.de; Doetinchem, P. von, ; Duranti, M., ; Gast, H., ; Karpinski, W., ; Kirn, T., ; Lübelsmeyer, K., ; Maña, C., ; Marrocchesi, P.S., ; Mertsch, P., ; Moskalenko, I.V., ; Schervan, T., ; Schluse, M., ; Schröder, K.-U., ; Schultz von Dratzig, A., ; Senatore, C., ; Spies, L., ; Wakely, S.P., ; Wlochal, M., ; Uglietti, D., ; Zimmermann, J., AMS-100: The next generation magnetic spectrometer in space - An international science platform for physics and astrophysics at Lagrange point 2 Amsterdam Elsevier 2019 Nuclear Instruments and Methods in Physics Research Section A: Accelerators, Spectrometers, Detectors and Associated Equipment 944 162561 10.1016/j.nima.2019.162561 bezahl https://doi.org/10.1016/j.nima.2019.162561 Fachbereich Luft- und Raumfahrttechnik OPUS4-9374 Wissenschaftlicher Artikel Seefeldt, Patric, ; Dachwald, Bernd, dachwald@fh-aachen.de Temperature increase on folded solar sail membranes Amsterdam Elsevier 2021 7 Advances in Space Research 67 9 2688 2695 10.1016/j.asr.2020.09.026 bezahl https://doi.org/10.1016/j.asr.2020.09.026 Fachbereich Luft- und Raumfahrttechnik OPUS4-9582 Bericht Blandford, Daniel, ; Dachwald, Bernd, dachwald@fh-aachen.de; Digel, Ilya, digel@fh-aachen.de; Espe, Clemens, c.espe@fh-aachen.de; Feldmann, Marco, feldmann@fh-aachen.de; Francke, Gero, francke@fh-aachen.de; Hiecke, Hannah, mail@HannahHiecke.de; Kowalski, Julia, kowalski@fh-aachen.de; Lindner, Peter, ; Plescher, Engelbert, plescher@fh-aachen.de; Schöngarth, Sarah, Enceladus Explorer : Schlussbericht — Version: 1.0 Aachen FH Aachen 2015 Förderkennzeichen BMWi 50NA1206 10.2314/GBV:86319950X weltweit https://doi.org/10.2314/GBV:86319950X Fachbereich Medizintechnik und Technomathematik OPUS4-10067 Konferenzveröffentlichung Dachwald, Bernd, Dachwald@fh-aachen.de; Kahle, Ralph, ; Wie, Bong, Solar sail Kinetic Energy Impactor (KEI) mission design tradeoffs for impacting and deflecting asteroid 99942 Apophis Near-Earth asteroid 99942 Apophis provides a typical example for the evolution of asteroid orbits that lead to Earth-impacts after a close Earth-encounter that results in a resonant return. Apophis will have a close Earth-encounter in 2029 with potential very close subsequent Earth-encounters (or even an impact) in 2036 or later, depending on whether it passes through one of several so-called gravitational keyholes during its 2029-encounter. Several pre-2029-deflection scenarios to prevent Apophis from doing this have been investigated so far. Because the keyholes are less than 1 km in size, a pre-2029 kinetic impact is clearly the best option because it requires only a small change in Apophis' orbit to nudge it out of a keyhole. A single solar sail Kinetic Energy Impactor (KEI) spacecraft that impacts Apophis from a retrograde trajectory with a very high relative velocity (75-80 km/s) during one of its perihelion passages at about 0.75 AU would be a feasible option to do this. The spacecraft consists of a 160 m x 160 m, 168 kg solar sail assembly and a 150 kg impactor. Although conventional spacecraft can also achieve the required minimum deflection of 1 km for this approx. 320 m-sized object from a prograde trajectory, our solar sail KEI concept also allows the deflection of larger objects. In this paper, we also show that, even after Apophis has flown through one of the gravitational keyholes in 2029, solar sail Kinetic Energy Impactor (KEI) spacecraft are still a feasible option to prevent Apophis from impacting the Earth, but many KEIs would be required for consecutive impacts to increase the total Earth-miss distance to a safe value. In this paper, we elaborate potential pre- and post-2029 KEI impact scenarios for a launch in 2020, and investigate tradeoffs between different mission parameters. 2006 20 AIAA/AAS Astrodynamics Specialist Conference and Exhibit AIAA/AAS Astrodynamics Specialist Conference and Exhibit, 21 August 2006 - 24 August 2006, Keystone, Colorado(USA). 1 20 10.2514/6.2006-6178 https://doi.org/10.2514/6.2006-6178 Fachbereich Luft- und Raumfahrttechnik OPUS4-10073 Konferenzveröffentlichung Grundmann, Jan Thimo, ; Bauer, Waldemar, ; Boden, Ralf Christian, ; Ceriotti, Matteo, ; Cordero, Federico, ; Dachwald, Bernd, ; Dumont, Etienne, ; Grimm, Christian D., ; Hercik, D., ; Herique, A., ; Ho, Tra-Mi, ; Jahnke, Rico, ; Kofman, Wlodek, ; Lange, Caroline, ; Lichtenheldt, Roy, ; McInnes, Colin R., ; Mikschl, Tobias, ; Mikulz, Eugen, ; Montenegro, Sergio, ; Moore, Iain, ; Pelivan, Ivanka, ; Peloni, Alessandro, ; Plettemeier, Dirk, ; Quantius, Dominik, ; Reershemius, Siebo, ; Renger, Thomas, ; Riemann, Johannes, ; Rogez, Yves, ; Ruffer, Michael, ; Sasaki, Kaname, ; Schmitz, Nicole, ; Seboldt, Wolfgang, ; Seefeldt, Patric, ; Spietz, Peter, ; Spröwitz, Tom, ; Sznajder, Maciej, ; Toth, Norbert, ; Viavattene, Giulia, ; Wejmo, Elisabet, ; Wolff, Friederike, ; Ziach, Christian, Responsive integrated small spacecraft solar sail and payload design concepts and missions Asteroid mining has the potential to greatly reduce the cost of in-space manufacturing, production of propellant for space transportation and consumables for crewed spacecraft, compared to launching the required resources from Earth's deep gravity well. This paper discusses the top-level mission architecture and trajectory design for these resource-return missions, comparing high-thrust trajectories with continuous low-thrust solar-sail trajectories. This work focuses on maximizing the economic Net Present Value, which takes the time-cost of finance into account and therefore balances the returned resource mass and mission duration. The different propulsion methods will then be compared in terms of maximum economic return, sets of attainable target asteroids, and mission flexibility. This paper provides one more step towards making commercial asteroid mining an economically viable reality by integrating trajectory design, propulsion technology and economic modelling. 2019 Conference: 5th International Symposium on Solar Sailing (ISSS 2019) Conference: 5th International Symposium on Solar Sailing (ISSS 2019)At: Aachen, Germany https://www.researchgate.net/publication/334964831_Responsive_integrated_small_spacecraft_solar_sail_and_payload_design_concepts_and_missions Fachbereich Luft- und Raumfahrttechnik OPUS4-10076 Konferenzveröffentlichung Grundmann, Jan Thimo, ; Bauer, Waldemar, ; Biele, Jens, ; Boden, Ralf, ; Ceriotti, Matteo, ; Cordero, Federico, ; Dachwald, Bernd, Dachwald@fh-aachen.de; 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, ; Ziach, Christian, Small spacecraft based multiple near-earth asteroid rendezvous and landing with near-term solar sails and 'Now-Term 'technologies Physical interaction with small solar system bodies (SSSB) is the next step in planetary science, planetary in-situ resource utilization (ISRU), and planetary defense (PD). It requires a broader understanding of the surface properties of the target objects, with particular interest focused on those near Earth. Knowledge of composition, multi-scale surface structure, thermal response, and interior structure is required to design, validate and operate missions addressing these three fields. The current level of understanding is occasionally simplified into the phrase, "If you've seen one asteroid, you've seen one asteroid", meaning that the in-situ characterization of SSSBs has yet to cross the threshold towards a robust and stable scheme of classification. This would enable generic features in spacecraft design, particularly for ISRU and science missions. Currently, it is necessary to characterize any potential target object sufficiently by a dedicated pre-cursor mission to design the mission which then interacts with the object in a complex fashion. To open up strategic approaches, much broader in-depth characterization of potential target objects would be highly desirable. In SSSB science missions, MASCOT-like nano-landers and instrument carriers which integrate at the instrument level to their mothership have met interest. By its size, MASCOT is compatible with small interplanetary missions. The DLR-ESTEC Gossamer Roadmap Science Working Groups' studies identified Multiple Near-Earth asteroid (NEA) Rendezvous (MNR) as one of the space science missions only feasible with solar sail propulsion. The Solar Polar Orbiter (SPO) study showed the ability to access any inclination, theDisplaced-L1 (DL1) mission operates close to Earth, where objects of interest to PD and for ISRU reside. Other studies outline the unique capability of solar sails to provide access to all SSSB, at least within the orbit of Jupiter, and significant progress has been made to explore the performance envelope of near-term solar sails for MNR. However, it is difficult for sailcraft to interact physically with a SSSB. We expand and extend the philosophy of the recently qualified DLR Gossamer solar sail deployment technology using efficient multiple sub-spacecraft integration to also include landers for one-way in-situ investigations and sample-return missions by synergetic integration and operation of sail and lander. The MASCOT design concept and its characteristic features have created an ideal counterpart for thisand has already been adapted to the needs of the AIM spacecraft, former part of the NASA-ESA AIDA missionDesigning the 69th International Astronautical Congress (IAC), Bremen, Germany, 1-5 October 2018. IAC-18-F1.2.3 Page 2 of 17 combined spacecraft for piggy-back launch accommodation enables low-cost massively parallel access to the NEA population. 2018 18 69 th International Astronautical Congress (IAC) 69th International Astronautical Congress (IAC), Bremen, Germany, 1-5 October 2018. https://www.bho-legal.com/1-5-october-2018-69th-international-astronautical-congress-2018-in-bremen-germany/ 1 18 weltweit https://eprints.gla.ac.uk/169536/7/169536.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-10077 Konferenzveröffentlichung Loeb, Horst W., ; Schartner, Karl-Heinz, ; Seboldt, Wolfgang, ; Dachwald, Bernd, Dachwald@fh-aachen.de; Streppel, Joern, ; Meusemann, Hans, ; Schülke, Peter, SEP for a lander mission to the jovian moon europa Under DLR-contract, Giessen University and DLR Cologne are studying solar-electric propulsion missions (SEP) to the outer regions of the solar system. The most challenging reference mission concerns the transport of a 1.35-tons chemical lander spacecraft into an 80-RJ circular orbit around Jupiter, which would enable to place a 375 kg lander with 50 kg of scientific instruments on the surface of the icy moon "Europa". Thorough analyses show that the best solution in terms of SEP launch mass times thrusting time would be a two-stage EP module and a triple-junction solar array with concentrators which would be deployed step by step. Mission performance optimizations suggest to propel the spacecraft in the first EP stage by 6 gridded ion thrusters, running at 4.0 kV of beam voltage, which would save launch mass, and in the second stage by 4 thrusters with 1.25 to 1.5 kV of positive high voltage saving thrusting time. In this way, the launch mass of the spacecraft would be kept within 5.3 tons. Without a launcher's C3 and interplanetary gravity assists, Jupiter might be reached within about 4 yrs. The spiraling-down into the parking orbit would need another 1.8 yrs. This "large mission" can be scaled down to a smaller one, e.g., by halving all masses, the solar array power, and the number of thrusters. Due to their reliability, long lifetime and easy control, RIT-22 engines have been chosen for mission analysis. Based on precise tests, the thruster performance has been modeled. 2006 12 57th International Astronautical Congress 57th International Astronautical Congress, 02 October 2006 - 06 October 2006, Valencia, Spain. 1 12 10.2514/6.IAC-06-C4.4.04 weltweit https://doi.org/10.2514/6.IAC-06-C4.4.04 Fachbereich Luft- und Raumfahrttechnik OPUS4-10091 Konferenzveröffentlichung Dachwald, Bernd, Dachwald@fh-aachen.de Global optimization of low-thrust space missions using evolutionary neurocontrol Low-thrust space propulsion systems enable flexible high-energy deep space missions, but the design and optimization of the interplanetary transfer trajectory is usually difficult. It involves much experience and expert knowledge because the convergence behavior of traditional local trajectory optimization methods depends strongly on an adequate initial guess. Within this extended abstract, evolutionary neurocontrol, a method that fuses artificial neural networks and evolutionary algorithms, is proposed as a smart global method for low-thrust trajectory optimization. It does not require an initial guess. The implementation of evolutionary neurocontrol is detailed and its performance is shown for an exemplary mission. 2005 6 Proceedings of the international workshop on global optimization 85 90 Fachbereich Luft- und Raumfahrttechnik OPUS4-10093 Konferenzveröffentlichung Grundmann, Jan Thimo, ; Borella, Laura, ; Ceriotti, Matteo, ; Chand, Suditi, ; Cordero, Federico, ; Dachwald, Bernd, Dachwald@fh-aachen.de; Fexer, Sebastian, ; Grimm, Christian D., ; Hendrikse, Jeffrey, ; Herčík, David, ; Herique, Alain, ; Hillebrandt, Martin, ; Ho, Tra-Mi, ; Kesseler, Lars, ; Laabs, Martin, ; Lange, Caroline, ; Lange, Michael, ; Lichtenheldt, Roy, ; McInnes, Colin R., ; Moore, Iain, ; Peloni, Alessandro, ; Plettenmeier, Dirk, ; Quantius, Dominik, ; Seefeldt, Patric, ; Venditti, Flaviane c. F., ; Vergaaij, Merel, ; Viavattene, Giulia, ; Virkki, Anne K., ; Zander, Martin, More bucks for the bang: new space solutions, impact tourism and one unique science & engineering opportunity at T-6 months and counting 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 (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 kicked off another headline-grabbing media scare or wants to keep civil defense very idle very soon, chances are that it will hit (note: this is an exercise!). Taking stock, it is barely 6 months to impact, a steadily rising likelihood that it will actually happen, and a huge uncertainty of possible impact energies: First estimates range from 1.2 MtTNT to 13 GtTNT, and this is not even the worst-worst case: a 700 m diameter massive NiFe asteroid (covered by a thin veneer of Ryugu-black rubble to match size and brightness), would come in at 70 GtTNT. In down to Earth terms, this could be all between smashing fireworks over some remote area of the globe and a 7.5 km crater downtown somewhere. Considering the deliberate and sedate ways of development of interplanetary missions it seems we can only stand and stare until we know well enough where to tell people to pack up all that can be moved at all and save themselves. But then, it could just as well be a smaller bright rock. The best estimate is 120 m diameter from optical observation alone, by 13% standard albedo. NASA's upcoming DART mission to binary asteroid (65803) Didymos is designed to hit such a small target, its moonlet Dimorphos. The Deep Impact mission's impactor in 2005 successfully guided itself to the brightest spot on comet 9P/Tempel 1, a relatively small feature on the 6 km nucleus. And 'space' has changed: By the end of this decade, one satellite communication network plans to have launched over 11000 satellites at a pace of 60 per launch every other week. This level of series production is comparable in numbers to the most prolific commercial airliners. Launch vehicle production has not simply increased correspondingly - they can be reused, although in a trade for performance. Optical and radio astronomy as well as planetary radar have made great strides in the past decade, and so has the design and production capability for everyday 'high-tech' products. 60 years ago, spaceflight was invented from scratch within two years, and there are recent examples of fast-paced space projects as well as a drive towards 'responsive space'. It seems it is not quite yet time to abandon all hope. We present what could be done and what is too close to call once thinking is shoved out of the box by a clear and present danger, to show where a little more preparedness or routine would come in handy - or become decisive. And if we fail, let's stand and stare safely and well instrumented anywhere on Earth together in the greatest adventure of science. 2021 7th IAA Planetary Defense Conference 7th IAA Planetary Defense Conference, Vienna, Austria, 26-30 April 2021 https://iaaspace.org/event/8th-iaa-planetary-defense-conference-2023/ Fachbereich Luft- und Raumfahrttechnik OPUS4-10094 Konferenzveröffentlichung Jean-Pierre P., de Vera, ; Baque, Mickael, ; Billi, Daniela, ; Böttger, Ute, ; Bulat, Sergey, ; Czupalla, Markus, ; Dachwald, Bernd, Dachwald@fh-aachen.de; de la Torre, Rosa, ; Elsaesser, Andreas, ; Foucher, Frédéric, ; Korsitzky, Hartmut, ; Kozyrovska, Natalia, ; Läufer, Andreas, ; Moeller, Ralf, ; Olsson-Francis, Karen, ; Onofri, Silvano, ; Sommer, Stefan, ; Wagner, Dirk, ; Westall, Frances, The search for life on Mars and in the Solar System - strategies, logistics and infrastructures The question "Are we alone in the Universe?" is perhaps the most fundamental one that affects mankind. How can we address the search for life in our Solar System? Mars, Enceladus and Europa are the focus of the search for life outside the terrestrial biosphere. While it is more likely to find remnants of life (fossils of extinct life) on Mars because of its past short time window of the surface habitability, it is probably more likely to find traces of extant life on the icy moons and ocean worlds of Jupiter and Saturn. Nevertheless, even on Mars there could still be a chance to find extant life in niches near to the surface or in just discovered subglacial lakes beneath the South Pole ice cap. Here, the different approaches for the detection of traces of life in the form of biosignatures including pre-biotic molecules will be presented. We will outline the required infrastructure for this enterprise and give examples of future mission concepts to investigate the presence of life on other planets and moons. Finally, we will provide suggestions on methods, techniques, operations and strategies for preparation and realization of future life detection missions. 2018 8 69th International Astronautical Congress (IAC) 69th International Astronautical Congress (IAC), Bremen, Germany, 1-5 October 2018. 1 8 weltweit https://elib.dlr.de/129886/1/IAC-18%2CA1%2C6%2C12%2Cx44662.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-10095 Konferenzveröffentlichung Grundmann, Jan Thimo, ; Bauer, Waldemar, ; Biele, Jens, ; Boden, Ralf, ; Ceriotti, Matteo, ; Cordero, Federico, ; Dachwald, Bernd, ; Dumont, Etienne, ; Grimm, Christian, ; Herčík, David, ; Herique, Alain, ; Ho, Tra-Mi, ; Jahnke, Rico, ; Koch, Aaron, ; Kofman, Wlodek, ; Koncz, Alexander, ; Krause, Christian, ; Lange, Caroline, ; Lichtenheldt, Roy, ; Maiwald, Volker, ; Mikschl, Tobias, ; Mikulz, Eugen, ; Montenegro, Sergio, ; Pelivan, Ivanka, ; Peloni, Alessandro, ; Plettemeier, Dirk, ; 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, ; Toth, Norbert, ; Wejmo, Elisabet, ; Wolff, Friederike, ; Ziach, Christian, Efficient massively parallel prospection for ISRU by multiple near-earth asteroid rendezvous using near-term solar sails and'now-term'small spacecraft solutions Physical interaction with small solar system bodies (SSSB) is key for in-situ resource utilization (ISRU). The design of mining missions requires good understanding of SSSB properties, including composition, surface and interior structure, and thermal environment. But as the saying goes "If you've seen one asteroid, you've seen one Asteroid": Although some patterns may begin to appear, a stable and reliable scheme of SSSB classification still has to be evolved. Identified commonalities would enable generic ISRU technology and spacecraft design approaches with a high degree of re-use. Strategic approaches require much broader in-depth characterization of the SSSB populations of interest to the ISRU community. The DLR-ESTEC GOSSAMER Roadmap Science Working Groups identified target-flexible Multiple Near-Earth asteroid (NEA) Rendezvous (MNR) as one of the missions only feasible with solar sail propulsion, showed the ability to access any inclination and a wide range of heliocentric distances as well as continuous operation close to Earth's orbit where low delta-v objects reside. 2018 33 2nd Asteroid Science Intersections with In-Space Mine Engineering – ASIME 2018 2nd Asteroid Science Intersections with In-Space Mine Engineering - ASIME 2018 16-17 April 2018, Belval, Luxembourg 1 33 weltweit https://elib.dlr.de/121960/2/EfficientProspectionByMultipleNEArendezvousSolarSailSmallSpacecraft_presentation_ASIME2018_2018-04-17_1530_pres.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-10096 Konferenzveröffentlichung Carzana, Livio, ; Dachwald, Bernd, Dachwald@fh-aachen.de; Noomen, Ron, Model and trajectory optimization for an ideal laser-enhanced solar sail A laser-enhanced solar sail is a solar sail that is not solely propelled by solar radiation but additionally by a laser beam that illuminates the sail. This way, the propulsive acceleration of the sail results from the combined action of the solar and the laser radiation pressure onto the sail. The potential source of the laser beam is a laser satellite that coverts solar power (in the inner solar system) or nuclear power (in the outer solar system) into laser power. Such a laser satellite (or many of them) can orbit anywhere in the solar system and its optimal orbit (or their optimal orbits) for a given mission is a subject for future research. This contribution provides the model for an ideal laser-enhanced solar sail and investigates how a laser can enhance the thrusting capability of such a sail. The term "ideal" means that the solar sail is assumed to be perfectly reflecting and that the laser beam is assumed to have a constant areal power density over the whole sail area. Since a laser beam has a limited divergence, it can provide radiation pressure at much larger solar distances and increase the radiation pressure force into the desired direction. Therefore, laser-enhanced solar sails may make missions feasible, that would otherwise have prohibitively long flight times, e.g. rendezvous missions in the outer solar system. This contribution will also analyze exemplary mission scenarios and present optimial trajectories without laying too much emphasis on the design and operations of the laser satellites. If the mission studies conclude that laser-enhanced solar sails would have advantages with respect to "traditional" solar sails, a detailed study of the laser satellites and the whole system architecture would be the second next step 2017 68th International Astronautical Congress 68th International Astronautical Congress: Unlocking Imagination, Fostering Innovation and Strengthening Security, IAC 2017, 2017-09-25 → 2017-09-29, Adelaide, Australia Fachbereich Luft- und Raumfahrttechnik OPUS4-10099 Konferenzveröffentlichung Dachwald, Bernd, Low-Thrust Mission Analysis and Global Trajectory Optimization Using Evolutionary Neurocontrol: New Results Interplanetary trajectories for low-thrust spacecraft are often characterized by multiple revolutions around the sun. Unfortunately, the convergence of traditional trajectory optimizers that are based on numerical optimal control methods depends strongly on an adequate initial guess for the control function (if a direct method is used) or for the starting values of the adjoint vector (if an indirect method is used). Especially when many revolutions around the sun are re- quired, trajectory optimization becomes a very difficult and time-consuming task that involves a lot of experience and expert knowledge in astrodynamics and optimal control theory, because an adequate initial guess is extremely hard to find. Evolutionary neurocontrol (ENC) was proposed as a smart method for low-thrust trajectory optimization that fuses artificial neural networks and evolutionary algorithms to so-called evolutionary neurocontrollers (ENCs) [1]. Inspired by natural archetypes, ENC attacks the trajectoryoptimization problem from the perspective of artificial intelligence and machine learning, a perspective that is quite different from that of optimal control theory. Within the context of ENC, a trajectory is regarded as the result of a spacecraft steering strategy that maps permanently the actual spacecraft state and the actual target state onto the actual spacecraft control vector. This way, the problem of searching the optimal spacecraft trajectory is equivalent to the problem of searching (or "learning") the optimal spacecraft steering strategy. An artificial neural network is used to implement such a spacecraft steering strategy. It can be regarded as a parameterized function (the network function) that is defined by the internal network parameters. Therefore, each distinct set of network parameters defines a different network function and thus a different steering strategy. The problem of searching the optimal steering strategy is now equivalent to the problem of searching the optimal set of network parameters. Evolutionary algorithms that work on a population of (artificial) chromosomes are used to find the optimal network parameters, because the parameters can be easily mapped onto a chromosome. The trajectory optimization problem is solved when the optimal chromosome is found. A comparison of solar sail trajectories that have been published by others [2, 3, 4, 5] with ENC-trajectories has shown that ENCs can be successfully applied for near-globally optimal spacecraft control [1, 6] and that they are able to find trajectories that are closer to the (unknown) global optimum, because they explore the trajectory search space more exhaustively than a human expert can do. The obtained trajectories are fairly accurate with respect to the terminal constraint. If a more accurate trajectory is required, the ENC-solution can be used as an initial guess for a local trajectory optimization method. Using ENC, low-thrust trajectories can be optimized without an initial guess and without expert attendance. Here, new results for nuclear electric spacecraft and for solar sail spacecraft are presented and it will be shown that ENCs find very good trajectories even for very difficult problems. Trajectory optimization results are presented for 1. NASA's Solar Polar Imager Mission, a mission to attain a highly inclined close solar orbit with a solar sail [7] 2. a mission to de ect asteroid Apophis with a solar sail from a retrograde orbit with a very-high velocity impact [8, 9] 3. JPL's \2nd Global Trajectory Optimization Competition", a grand tour to visit four asteroids from different classes with a NEP spacecraft 2007 European Workshop on Space Mission Analysis ESA/ESOC, Darmstadt, Germany 10 { 12 Dec 2007 Fachbereich Luft- und Raumfahrttechnik OPUS4-10100 Konferenzveröffentlichung Dachwald, Bernd, Dachwald@fh-aachen.de; Xu, Changsheng, ; Feldmann, Marco, ; Plescher, Engelbert, IceMole : Development of a novel subsurface ice probe and testing of the first prototype on the Morteratsch Glacier We present the novel concept of a combined drilling and melting probe for subsurface ice research. This probe, named "IceMole", is currently developed, built, and tested at the FH Aachen University of Applied Sciences' Astronautical Laboratory. Here, we describe its first prototype design and report the results of its field tests on the Swiss Morteratsch glacier. Although the IceMole design is currently adapted to terrestrial glaciers and ice shields, it may later be modified for the subsurface in-situ investigation of extraterrestrial ice, e.g., on Mars, Europa, and Enceladus. If life exists on those bodies, it may be present in the ice (as life can also be found in the deep ice of Earth). 2011 EGU General Assembly 2011 Vienna | Austria | 03 – 08 April 2011 weltweit https://meetingorganizer.copernicus.org/EGU2011/EGU2011-4943.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-10101 Konferenzveröffentlichung Grundmann, Jan Thimo, ; Biele, Jens, ; Dachwald, Bernd, Dachwald@fh-aachen.de; Grimm, Christian, ; Lange, Caroline, ; Ulamec, Stephan, Small spacecraft for small solar system body science, planetary defence and applications Following the recent successful landings and occasional re-awakenings of PHILAE, the lander carried aboard ROSETTA to comet 67P/Churyumov-Gerasimenko, and the launch of the Mobile Asteroid Surface Scout, MASCOT, aboard the HAYABUSA2 space probe to asteroid (162173) Ryugu we present an overview of the characteristics and peculiarities of small spacecraft missions to small solar system bodies (SSSB). Their main purpose is planetary science which is transitioning from a 'pure' science of observation of the distant to one also supporting in-situ applications relevant for life on Earth. Here we focus on missions at the interface of SSSB science and planetary defence applications. We provide a brief overview of small spacecraft SSSB missions and on this background present recent missions, projects and related studies at the German Aerospace Center, DLR, that contribute to the worldwide planetary defence community. These range from Earth orbit technology demonstrators to active science missions in interplanetary space. We provide a summary of experience from recently flown missions with DLR participation as well as a number of studies. These include PHILAE, the lander of ESA's ROSETTA comet rendezvous mission now on the surface of comet 67P/Churyumov-Gerasimenko, and the Mobile Asteroid Surface Scout, MASCOT, now in cruise to the ~1 km diameter C-type near-Earth asteroid (162173) Ryugu aboard the Japanese sample-return probe HAYABUSA2. We introduce the differences between the conventional methods employed in the design, integration and testing of large spacecraft and the new approaches developed by small spacecraft projects. We expect that the practical experience that can be gained from projects on extremely compressed timelines or with high-intensity operation phases on a newly explored small solar system body can contribute significantly to the study, preparation and realization of future planetary defence related missions. One is AIDA (Asteroid Impact & Deflection Assessment), a joint effort of ESA, JHU/APL, NASA, OCA and DLR, combining JHU/APL's DART (Double Asteroid Redirection Test) and ESA's AIM (Asteroid Impact Monitor) spacecraft in a mission towards near-Earth binary asteroid system (65803) Didymos. DLR is currently applying MASCOT heritage and lessons learned to the design of MASCOT2, a lander for the AIM mission to support a bistatic low frequency radar experiment with PHILAE/ROSETTA CONSERT heritage to explore the inner structure of Didymoon which is the designated impact target for DART. 2016 1-20 IEEE Aerospace Conference 2016 Link "https://arc.aiaa.org/doi/book/10.2514/MGNC05" am 15.07.2022 von Behr hinzugefügt. 1 20 weltweit https://elib.dlr.de/111157/2/SmallSpacecraftForSSSBscienceAndApplications_paper_IEEE2016_2016-01-11newCVcg_ID2386_2-1205_READBACK2016-02-20_2057.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-10016 Konferenzveröffentlichung Grundmann, Jan Thimo, ; Biele, Jens, ; Dachwald, Bernd, Dachwald@fh-aachen.de; Grimm, Christian D., ; Lange, Caroline, ; Ulamec, Stephan, ; Ziach, Christian, ; Spröwitz, Tom, ; Ruffer, Michael, ; Seefeldt, Patric, ; Spietz, Peter, ; Toth, Norbert, ; Mimasu, Yuya, ; Rittweger, Andreas, ; Bibring, Jean-Pierre, ; Braukhane, Andy, ; Boden, Ralf Christian, ; Dumont, Etienne, ; Jahnke, Stephan Siegfried, ; Jetzschmann, Michael, ; Krüger, Hans, ; Lange, Michael, ; Gomez, Antonio Martelo, ; Massonett, Didier, ; Okada, Tatsuaki, ; Sagliano, Marco, ; Sasaki, Kaname, ; Schröder, Silvio, ; Sippel, Martin, ; Skoczylas, Thomas, ; Wejmo, Elisabet, Small landers and separable sub-spacecraft for near-term solar sails Following the successful PHILAE landing with ESA's ROSETTA probe and the launch of the MINERVA rovers and the Mobile Asteroid Surface Scout, MASCOT, aboard the JAXA space probe, HAYABUSA2, to asteroid (162173) Ryugu, small landers have found increasing interest. Integrated at the instrument level in their mothership they support small solar system body studies. With efficient capabilities, resource-friendly design and inherent robustness they are an attractive exploration mission element. We discuss advantages and constraints of small sub-spacecraft, focusing on emerging areas of activity such as asteroid diversity studies, planetary defence, and asteroid mining, on the background of our projects PHILAE, MASCOT, MASCOT2, the JAXA-DLR Solar Power Sail Lander Design Study, and others. The GOSSAMER-1 solar sail deployment concept also involves independent separable sub-spacecraft operating synchronized to deploy the sail. Small spacecraft require big changes in the way we do things and occasionally a little more effort than would be anticipated based on a traditional large spacecraft approach. In a Constraints-Driven Engineering environment we apply Concurrent Design and Engineering (CD/CE), Concurrent Assembly, Integration and Verification (CAIV) and Model-Based Systems Engineering (MBSE). Near-term solar sails will likely be small spacecraft which we expect to harmonize well with nano-scale separable instrument payload packages. 2017 10 The Fourth International Symposium on Solar Sailing 2017 The Fourth International Symposium on Solar Sailing 2017, 17-20 January 2017. Kyoto Research Park, Kyoto, Japan 1 10 weltweit https://elib.dlr.de/118803/1/17094_Paper_Mr.%20Jan%20Thimo%20Grundmann.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-10045 Konferenzveröffentlichung Peloni, Alessandro, ; Dachwald, Bernd, Dachwald@fh-aachen.de; Ceriotti, Matteo, Multiple NEA rendezvous mission: Solar sailing options The scientific interest in near-Earth asteroids (NEAs) and the classification of some of those as potentially hazardous asteroid for the Earth stipulated the interest in NEA exploration. Close-up observations of these objects will increase drastically our knowledge about the overall NEA population. For this reason, a multiple NEA rendezvous mission through solar sailing is investigated, taking advantage of the propellantless nature of this groundbreaking propulsion technology. Considering a spacecraft based on the DLR/ESA Gossamer technology, this work focuses on the search of possible sequences of NEA encounters. The effectiveness of this approach is demonstrated through a number of fully-optimized trajectories. The results show that it is possible to visit five NEAs within 10 years with near-term solar-sail technology. Moreover, a study on a reduced NEA database demonstrates the reliability of the approach used, showing that 58% of the sequences found with an approximated trajectory model can be converted into real solar-sail trajectories. Lastly, this second study shows the effectiveness of the proposed automatic optimization algorithm, which is able to find solutions for a large number of mission scenarios without any input required from the user. 2017 11 Fourth International Symposium on Solar Sailing Fourth International Symposium on Solar Sailing (ISSS 2017), Kyoto, Japan, 17-20 Jan 2017. http://www.jsforum.or.jp/ISSS2017/ 1 11 weltweit https://eprints.gla.ac.uk/135222/1/135222.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-10049 Konferenzveröffentlichung Grundmann, Jan Thimo, ; Lange, Caroline, ; Dachwald, Bernd, Dachwald@fh-aachen.de; Grimm, Christian, ; Koch, Aaron, ; Ulamec, Stephan, Small Spacecraft in Planetary Defence Related Applications-Capabilities, Constraints, Challenges In this paper we present an overview of the characteristics and peculiarities of small spacecraft missions related to planetary defence applications. We provide a brief overview of small spacecraft missions to small solar system bodies. On this background we present recent missions and selected projects and related studies at the German Aerospace Center, DLR, that contribute to planetary defence related activities. These range from Earth orbit technology demonstrators to active science missions in interplanetary space. We provide a summary of experience from recently flown missions with DLR participation as well as a number of studies. These include PHILAE, the lander recently arrived on comet 67P/Churyumov-Gerasimenko aboard ESA's ROSETTA comet rendezvous mission, and the Mobile Asteroid Surface Scout, MASCOT, now underway to near-Earth asteroid (162173) 1999 JU3 aboard the Japanese sample-return probe HAYABUSA-2. We introduce the differences between the conventional methods employed in the design, integration and testing of large spacecraft and the new approaches developed by small spacecraft projects. We expect that the practical experience that can be gained from projects on extremely compressed timelines or with high-intensity operation phases on a newly explored small solar system body can contribute significantly to the study, preparation and realization of future planetary defence related missions. One is AIDA (Asteroid Impact & Deflection Assessment), a joint effort of ESA,JHU/APL, NASA, OCA and DLR, combining JHU/APL's DART (Double Asteroid Redirection Test) and ESA's AIM (Asteroid Impact Monitor) spacecraft in a mission towards near-Eath binary asteroid (65803) Didymos. 2015 18 IEEE Aerospace Conference 2015 IEEE Aerospace Conference, 7.-13. Mar. 2015, Big Sky, Montana, USA. 1 18 weltweit https://elib.dlr.de/103077/1/SmallSpacecraftInPlanetaryDefence_paper_IEEE2015_2015-01-22_2204_ID2363_TK-SN-SQ2-1211_READBACK.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-10055 Teil eines Buches Borggrafe, Andreas, ; Ohndorf, Andreas, ; Dachwald, Bernd, Dachwald@fh-aachen.de; Seboldt, Wolfgang, Analysis of interplanetary solar sail trajectories with attitude dynamics We present a new approach to the problem of optimal control of solar sails for low-thrust trajectory optimization. The objective was to find the required control torque magnitudes in order to steer a solar sail in interplanetary space. A new steering strategy, controlling the solar sail with generic torques applied about the spacecraft body axes, is integrated into the existing low-thrust trajectory optimization software InTrance. This software combines artificial neural networks and evolutionary algorithms to find steering strategies close to the global optimum without an initial guess. Furthermore, we implement a three rotational degree-of-freedom rigid-body attitude dynamics model to represent the solar sail in space. Two interplanetary transfers to Mars and Neptune are chosen to represent typical future solar sail mission scenarios. The results found with the new steering strategy are compared to the existing reference trajectories without attitude dynamics. The resulting control torques required to accomplish the missions are investigated, as they pose the primary requirements to a real on-board attitude control system. San Diego Univelt Inc 2012 16 Dynamics and Control of Space Systems 2012 978-0-87703-587-9 1553 1569 bezahl https://strathprints.strath.ac.uk/46642/1/Borggrafe_A_et_al_Pure_Analysis_of_interplanetary_solar_sail_trajectories_with_attitude_dynamics_2012.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-10034 Konferenzveröffentlichung Grundmann, Jan Thimo, ; Bauer, Waldemar, ; Boden, Ralf Christian, ; Ceriotti, Matteo, ; Cordero, Federico, ; Dachwald, Bernd, Dachwald@fh-aachen.de; Dumont, Etienne, ; Grimm, Christian D., ; Hercik, D., ; Herique, A., ; Ho, Tra-Mi, ; Jahnke, Rico, ; Kofman, Wlodek, ; Lange, Caroline, ; Lichtenheldt, Roy, ; McInnes, Colin R., ; Mikschl, Tobias, ; Montenegro, Sergio, ; Moore, Iain, ; Pelivan, Ivanka, ; Peloni, Alessandro, ; Plettenmeier, Dirk, ; Quantius, Dominik, ; Reershemius, Siebo, ; Renger, Thomas, ; Riemann, Johannes, ; Rogez, Yves, ; Ruffer, Michael, ; Sasaki, Kaname, ; Schmitz, Nicole, ; Seboldt, Wolfgang, ; Seefeldt, Patric, ; Spietz, Peter, ; Spröwitz, Tom, ; Sznajder, Maciej, ; Toth, Norbert, ; Viavattene, Giulia, ; Wejmo, Elisabet, ; Wolff, Friederike, ; Ziach, Christian, Responsive exploration and asteroid characterization through integrated solar sail and lander development using small spacecraft technologies In parallel to the evolution of the Planetary Defense Conference, the exploration of small solar system bodies has advanced from fast fly-bys on the sidelines of missions to the planets to the implementation of dedicated sample-return and in-situ analysis missions. Spacecraft of all sizes have landed, touch-and-go sampled, been gently beached, or impacted at hypervelocity on asteroid and comet surfaces. More have flown by close enough to image their surfaces in detail or sample their immediate environment, often as part of an extended or re-purposed mission. And finally, full-scale planetary defense experiment missions are in the making. Highly efficient low-thrust propulsion is increasingly applied beyond commercial use also in mainstream and flagship science missions, in combination with gravity assist propulsion. Another development in the same years is the growth of small spacecraft solutions, not in size but in numbers and individual capabilities. The on-going NASA OSIRIS-REx and JAXA HAYABUSA2 missions exemplify the trend as well as the upcoming NEA SCOUT mission or the landers MINERVA-II and MASCOT recently deployed on Ryugu. We outline likely as well as possible and efficient routes of continuation of all these developments towards a propellant-less and highly efficient class of spacecraft for small solar system body exploration: small spacecraft solar sails designed for carefree handling and equipped with carried landers and application modules, for all asteroid user communities -planetary science, planetary defence, and in-situ resource utilization. This projection 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 and in the 20 years since. It draws on the background of extensive trajectory optimization studies, the qualified technology of the DLR GOSSAMER-1 deployment demonstrator, and the MASCOT asteroid lander. These enable 'now-term' as well as near-term hardware solutions, and thus responsive fast-paced development. Mission types directly applicable to planetary defense include: single and Multiple NEA Rendezvous ((M)NR) for mitigation precursor, target monitoring and deflection follow-up tasks; sail-propelled head-on retrograde kinetic impactors (RKI) for mitigation; and deployable membrane based methods to modify the asteroid's properties or interact with it. The DLR-ESTEC GOSSAMER Roadmap 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 capability of near-term solar sails to achieve NEA rendezvous in any kind of orbit, from Earth-coorbital to extremely inclined and even retrograde orbits. For those mission types using separable payloads, such as SPO, (M)NR and RKI, 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 asteroids visited and enable multiple NEA sample-return missions. These are an ideal match for solar sails in micro-spacecraft format whose launch configurations are compatible with ESPA and ASAP secondary payload platforms. 2019 IAA Planetary Defense Conference Conference: IAA Planetary Defense ConferenceAt: Washington DC, USA 29.04-03.05.2019 https://www.researchgate.net/publication/335352701_Responsive_exploration_and_asteroid_characterization_through_integrated_solar_sail_and_lander_development_using_small_spacecraft_technologies Fachbereich Luft- und Raumfahrttechnik OPUS4-10079 Konferenzveröffentlichung Seboldt, Wolfgang, ; Blome, Hans-Joachim, ; Dachwald, Bernd, Dachwald@fh-aachen.de; Richter, Lutz, Proposal for an integrated European space exploration strategy Recently, in his vision for space exploration, US president Bush announced to extend human presence across the solar system, starting with a human return to the Moon as early as 2015 in preparation for human exploration of Mars and other destinations. In Europe, an exploration program, termed AURORA, was established by ESA in 2001 - funded on a voluntary basis by ESA member states - with a clear focus on Mars and the ultimate goal of landing humans on Mars around 2030 in international cooperation. In 2003, a Human Spaceflight Vision Group was appointed by ESA with the task to develop a vision for the role of human spaceflight during the next quarter of the century. The resulting vision focused on a European-led lunar exploration initiative as part of a multi-decade, international effort to strengthen European identity and economy. After a review of the situation in Europe concerning space exploration, the paper outlines an approach for a consistent positioning of exploration within the existing European space programs, identifies destinations, and develops corresponding scenarios for an integrated strategy, starting with robotic missions to the Moon, Mars, and near-Earth asteroids. The interests of the European planetary in-situ science community, which recently met at DLR Cologne, are considered. Potential robotic lunar missions comprise polar landings to search for frozen volatiles and a sample return. For Mars, the implementation of a modest robotic landing mission in 2009 to demonstrate the capability for landing and prepare more ambitious and complex missions is discussed. For near-Earth asteroid exploration, a low-cost in-situ technology demonstration mission could yield important results. All proposed scenarios offer excellent science and could therefore create synergies between ESA's mandatory and optional programs in the area of planetary science and exploration. The paper intents to stimulate the European discussion on space exploration and reflects the personal view of the authors. 2004 10 55th International Astronautical Congress of the International Astronautical Federation, the International Academy of Astronautics, and the International Institute of Space Law 55th International Astronautical Congress 2004 - Vancouver, Canada 1 10 weltweit https://www.researchgate.net/profile/Bernd-Dachwald/publication/225019767_Proposal_for_an_Integrated_European_Space_Exploration_Strategy/links/00463521c7257ab21f000000/Proposal-for-an-Integrated-European-Space-Exploration-Strategy.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-10087 Konferenzveröffentlichung Hallmann, Marcus, ; Heidecker, Ansgar, ; Schlotterer, Markus, ; Dachwald, Bernd, Dachwald@fh-aachen.de GTOC8: results and methods of team 15 DLR This paper describes the results and methods used during the 8th Global Trajectory Optimization Competition (GTOC) of the DLR team. Trajectory optimization is crucial for most of the space missions and usually can be formulated as a global optimization problem. A lot of research has been done to different type of mission problems. The most demanding ones are low thrust transfers with e.g. gravity assist sequences. In that case the optimal control problem is combined with an integer problem. In most of the GTOCs we apply a filtering of the problem based on domain knowledge. 2016 26th AAS/AIAA Space Flight Mechanics Meeting, Napa, CA 26th AAS/AIAA Space Flight Mechanics Meeting, February 14-18, 2016, Napa, California, U.S.A. Napa, CA Fachbereich Luft- und Raumfahrttechnik OPUS4-10088 Konferenzveröffentlichung Duprat, J., ; Dachwald, Bernd, Dachwald@fh-aachen.de; Hilchenbach, M., ; Engrand, Cecile, ; Espe, C., ; Feldmann, M., ; Francke, G., ; Görög, Mark, ; Lüsing, N., ; Langenhorst, Falko, The MARVIN project: a micrometeorite harvester in Antarctic snow MARVIN is an automated drilling and melting probe dedicated to collect pristine interplanetary dust particles (micrometeorites) from central Antarctica snow. 2013 44th Lunar and Planetary Science Conference 44th Lunar and Planetary Science Conference, March 18-22, 2013, The Woodlands, Texas https://www.researchgate.net/publication/258803463_The_MARVIN_Project_A_Micrometeorite_Harvester_in_Antarctic_Snow Fachbereich Luft- und Raumfahrttechnik OPUS4-10090 Konferenzveröffentlichung Dachwald, Bernd, Dachwald@fh-aachen.de; Seboldt, Wolfgang, ; Loeb, Horst W., ; Schartner, Karl-Heinz, A comparison of SEP and NEP for a main belt asteroid sample return mission Innovative interplanetary deep space missions, like a main belt asteroid sample return mission, require ever larger velocity increments (∆V s) and thus ever more demanding propulsion capabilities. Providing much larger exhaust velocities than chemical high-thrust systems, electric low-thrust space-propulsion systems can significantly enhance or even enable such high-energy missions. In 1995, a European-Russian Joint Study Group (JSG) presented a study report on "Advanced Interplanetary Missions Using Nuclear-Electric Propulsion" (NEP). One of the investigated reference missions was a sample return (SR) from the main belt asteroid (19) Fortuna. The envisaged nuclear power plant, Topaz-25, however, could not be realized and also the worldwide developments in space reactor hardware stalled. In this paper, we investigate, whether such a mission is also feasible using a solar electric propulsion (SEP) system and compare our SEP results to corresponding NEP results. 2007 10 7th International Symposium on Launcher Technologies, Barcelona, Spain, 02-05 April 2007 1 10 weltweit http://spacesailing.net/paper/200704_Barcelona_DachwaldSeboldtLoebSchartner.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-10066 Konferenzveröffentlichung Pirovano, Laura, ; Seefeldt, Patric, ; Dachwald, Bernd, ; Noomen, Ron, Attitude and orbital modeling of an uncontrolled solar-sail experiment in low-Earth orbit Gossamer-1 is the first project of the three-step Gossamer roadmap, the purpose of which is to develop, prove and demonstrate that solar-sail technology is a safe and reliable propulsion technique for long-lasting and high-energy missions. This paper firstly presents the structural analysis performed on the sail to understand its elastic behavior. The results are then used in attitude and orbital simulations. The model considers the main forces and torques that a satellite experiences in low-Earth orbit coupled with the sail deformation. Doing the simulations for varying initial conditions in attitude and rotation rate, the results show initial states to avoid and maximum rotation rates reached for correct and faulty deployment of the sail. Lastly comparisons with the classic flat sail model are carried out to test the hypothesis that the elastic behavior does play a role in the attitude and orbital behavior of the sail 2015 15 25th International Symposium on Space Flight Dynamics ISSFD 25th International Symposium on Space Flight Dynamics ISSFD October 19 - 23, 2015, Munich, Germany https://issfd.org/2015/ 1 15 weltweit https://elib.dlr.de/102965/1/079_Pirovano.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-10022 Konferenzveröffentlichung Loeb, Horst W., ; Schartner, Karl-Heinz, ; Dachwald, Bernd, Dachwald@fh-aachen.de; Ohndorf, Andreas, ; Seboldt, Wolfgang, An Interstellar - Heliopause mission using a combination of solar/radioisotope electric propulsion 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. 2011 7 Presented at the 32nd International Electric Propulsion Conference 32nd International Electric Propulsion Conference, 11-15 September. Wiesbaden, Germany 1 7 weltweit http://electricrocket.org/IEPC/IEPC-2011-052.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-10024 Konferenzveröffentlichung Dachwald, Bernd, Dachwald@fh-aachen.de; Baturkin, Volodymyr, ; Coverstone, Victoria, ; Diedrich, Ben, ; Garbe, Gregory, ; Görlich, Marianne, ; Leipold, Manfred, ; Lura, Franz, ; Macdonald, Malcolm, ; McInnes, Colin, ; Mengali, Giovanni, ; Quarta, Alessandro, ; Rios-Reyes, Leonel, ; Scheeres, Daniel J., ; Seboldt, Wolfgang, ; Wie, Bong, Potential effects of optical solar sail degredation on trajectory design The optical properties of the thin metalized polymer films that are projected for solar sails are assumed to be affected by the erosive effects of the space environment. Their degradation behavior in the real space environment, however, is to a considerable degree indefinite, because initial ground test results are controversial and relevant inspace tests have not been made so far. The standard optical solar sail models that are currently used for trajectory design do not take optical degradation into account, hence its potential effects on trajectory design have not been investigated so far. Nevertheless, optical degradation is important for high-fidelity solar sail mission design, because it decreases both the magnitude of the solar radiation pressure force acting on the sail and also the sail control authority. Therefore, we propose a simple parametric optical solar sail degradation model that describes the variation of the sail film's optical coefficients with time, depending on the sail film's environmental history, i.e., the radiation dose. The primary intention of our model is not to describe the exact behavior of specific film-coating combinations in the real space environment, but to provide a more general parametric framework for describing the general optical degradation behavior of solar sails. Using our model, the effects of different optical degradation behaviors on trajectory design are investigated for various exemplary missions. 2005 23 AAS/AIAA Astrodynamics Specialist 2005 AAS/AIAA Astrodynamics Specialist Conference, 7-11.08.2005. Lake Tahoe, California https://www.space-flight.org/AAS_meetings/2005_astro/2005_astro.html 1 23 weltweit https://strathprints.strath.ac.uk/6267/6/strathprints006267.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-8917 Teil eines Buches Dachwald, Bernd, dachwald@fh-aachen.de; Ohndorf, Andreas, Global optimization of continuous-thrust trajectories using evolutionary neurocontrol Searching optimal continuous-thrust trajectories is usually a difficult and time-consuming task. The solution quality of traditional optimal-control methods depends strongly on an adequate initial guess because the solution is typically close to the initial guess, which may be far from the (unknown) global optimum. Evolutionary neurocontrol attacks continuous-thrust optimization problems from the perspective of artificial intelligence and machine learning, combining artificial neural networks and evolutionary algorithms. This chapter describes the method and shows some example results for single- and multi-phase continuous-thrust trajectory optimization problems to assess its performance. Evolutionary neurocontrol can explore the trajectory search space more exhaustively than a human expert can do with traditional optimal-control methods. Especially for difficult problems, it usually finds solutions that are closer to the global optimum. Another fundamental advantage is that continuous-thrust trajectories can be optimized without an initial guess and without expert supervision. Cham Springer 2019 24 Modeling and Optimization in Space Engineering 978-3-030-10501-3 Springer Optimization and Its Applications, vol 144 gedruckt unter der Signatur 21 ZSS 46 in der Bereichsbibliothek Eupener Str. vorhanden 33 57 10.1007/978-3-030-10501-3_2 campus https://doi.org/10.1007/978-3-030-10501-3_2 Fachbereich Luft- und Raumfahrttechnik OPUS4-8862 Wissenschaftlicher Artikel Lyons, W. Berry, ; Mikucki, Jill A., ; German, Laura A., ; Welch, Kathleen A., ; Welch, Susan A., ; Gardener, Christopher B., ; Tulaczyk, Slawek M., ; Pettit, Erin C., ; Kowalski, Julia, kowalski@fh-aachen.de; Dachwald, Bernd, dachwald@fh-aachen.de The Geochemistry of Englacial Brine from Taylor Glacier, Antarctica Hoboken Wiley 2019 Journal of Geophysical Research: Biogeosciences 10.1029/2018JG004411 campus https://doi.org/10.1029/2018JG004411 Fachbereich Luft- und Raumfahrttechnik OPUS4-8863 Wissenschaftlicher Artikel Campen, R., ; Kowalski, Julia, kowalski@fh-aachen.de; Lyons, W.B., ; Tulaczyk, S., ; Dachwald, Bernd, dachwald@fh-aachen.de; Pettit, E., ; Welch, K. A., ; Mikucki, J.A., Microbial diversity of an Antarctic subglacial community and high-resolution replicate sampling inform hydrological connectivity in a polar desert Weinheim Wiley 2019 Environmental Microbiology accepted article 10.1111/1462-2920.14607 campus https://doi.org/10.1111/1462-2920.14607 Fachbereich Luft- und Raumfahrttechnik OPUS4-8852 Wissenschaftlicher Artikel Jan Thimo, Grundmann, ; Bauer, Waldemar, ; Biele, Jens, ; Boden, Ralf, ; Ceriotti, Matteo, ; Cordero, Federico, ; Dachwald, Bernd, dachwald@fh-aachen.de; Dumont, Etienne, ; Grimm, Christian D., ; Hercik, David, Capabilities of Gossamer-1 derived small spacecraft solar sails carrying Mascot-derived nanolanders for in-situ surveying of NEAs Amsterdam Elsevier 2019 32 Acta Astronautica 156 3 330 362 10.1016/j.actaastro.2018.03.019 bezahl https://doi.org/10.1016/j.actaastro.2018.03.019 Fachbereich Luft- und Raumfahrttechnik OPUS4-8857 Konferenzveröffentlichung Grundmann, Jan Thimo, ; Bauer, Waldemar, ; Borchers, Kai, ; Dumont, Etienne, ; Grimm, Christian D., ; Ho, Tra-Mi, ; Jahnke, Rico, ; Lange, Caroline, ; Maiwald, Volker, ; Mikulz, Eugen, ; Quantius, Dominik, ; Reershemius, Siebo, ; Renger, Thomas, ; Riemann, Johannes, ; Sasaki, Kaname, ; Seefeldt, Patric, ; Spietz, Peter, ; Spröwitz, Tom, ; Toth, Norbert, ; Wejmo, Elisabet, ; Biele, Jens, ; Krause, Christian, ; Cerotti, Matteo, ; Peloni, Alessandro, ; Dachwald, Bernd, dachwald@fh-aachen.de Small Spacecraft Solar Sailing for Small Solar System Body Multiple Rendezvous and Landing 2018 20 Seiten 2018 IEEE Aerospace Conference : 3-10 March 2018 978-1-5386-2014-4 weltweit https://elib.dlr.de/121956/1/SmallSpacecraftSolarSailingtoSSSB_paper_IEEE2018_2018-02-13.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-9174 Konferenzveröffentlichung Baader, Fabian, fabian.baader@fh-aachen.de; Keller, Denis, ; Lehmann, Raphael, ; Gerber, Lukas, ; Reiswich, Martin, ; Dachwald, Bernd, dachwald@fh-aachen.de; Förstner, Roger, Operating melting probes for ice penetration under sublimation conditions and in reduced gravity on a sounding rocket 2019 8 Seiten Proceedings of the 24th ESA Symposium on European Rocket and Balloon Programmes and related Research 24th PAC Symposium 2019 Fachbereich Luft- und Raumfahrttechnik OPUS4-9724 Wissenschaftlicher Artikel Heiligers, Jeannette, ; Schoutetens, Frederic, ; Dachwald, Bernd, dachwald@fh-aachen.de Photon-sail equilibria in the alpha centauri system 2021 8 Journal of Guidance, Control, and Dynamics 44 5 1053 1061 10.2514/1.G005446 bezahl https://doi.org/10.2514/1.G005446 Fachbereich Luft- und Raumfahrttechnik OPUS4-9725 Wissenschaftlicher Artikel German, Laura, ; Mikucki, Jill A., ; Welch, Susan A., ; Welch, Kathleen A., ; Lutton, Anthony, ; Dachwald, Bernd, dachwald@fh-aachen.de; Kowalski, Julia, kowalski@fh-aachen.de; Heinen, Dirk, ; Feldmann, Marco, feldmann@fh-aachen.de; Francke, Gero, francke@fh-aachen.de; Espe, Clemens, c.espe@fh-aachen.de; Lyons, W. Berry, Validation of sampling antarctic subglacial hypersaline waters with an electrothermal ice melting probe (IceMole) for environmental analytical geochemistry Geochemical characterisation of hypersaline waters is difficult as high concentrations of salts hinder the analysis of constituents at low concentrations, such as trace metals, and the collection of samples for trace metal analysis in natural waters can be easily contaminated. This is particularly the case if samples are collected by non-conventional techniques such as those required for aquatic subglacial environments. In this paper we present the first analysis of a subglacial brine from Taylor Valley, (~ 78°S), Antarctica for the trace metals: Ba, Co, Mo, Rb, Sr, V, and U. Samples were collected englacially using an electrothermal melting probe called the IceMole. This probe uses differential heating of a copper head as well as the probe's sidewalls and an ice screw at the melting head to move through glacier ice. Detailed blanks, meltwater, and subglacial brine samples were collected to evaluate the impact of the IceMole and the borehole pump, the melting and collection process, filtration, and storage on the geochemistry of the samples collected by this device. Comparisons between melt water profiles through the glacier ice and blank analysis, with published studies on ice geochemistry, suggest the potential for minor contributions of some species Rb, As, Co, Mn, Ni, NH4+, and NO2−+NO3− from the IceMole. The ability to conduct detailed chemical analyses of subglacial fluids collected with melting probes is critical for the future exploration of the hundreds of deep subglacial lakes in Antarctica. London Taylor & Francis 2021 13 International Journal of Environmental Analytical Chemistry 101 15 2654 2667 10.1080/03067319.2019.1704750 bezahl https://doi.org/10.1080/03067319.2019.1704750 Fachbereich Luft- und Raumfahrttechnik OPUS4-9726 Wissenschaftlicher Artikel 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, dachwald@fh-aachen.de; Macdonald, Malcolm, ; McInnes, Colin, ; Seboldt, Wolfgang, ; Quantius, Dominik, ; Bauer, Waldemar, ; Wiedemann, Carsten, ; Grimm, Christian D., ; Hercik, David, ; Ho, Tra-Mi, ; Lange, Caroline, ; Schmitz, Nicole, Paths not taken - The Gossamer roadmap's other options Amsterdam Elsevier 2021 44 Advances in Space Research 67 9 2912 2956 10.1016/j.asr.2021.01.044 campus https://doi.org/10.1016/j.asr.2021.01.044 Fachbereich Luft- und Raumfahrttechnik OPUS4-9728 Wissenschaftlicher Artikel Kezerashvili, Roman Ya, ; Dachwald, Bernd, dachwald@fh-aachen.de Preface: Solar sailing: Concepts, technology, and missions II Amsterdam Elsevier 2021 1 Advances in Space Research 67 9 2559 2560 10.1016/j.asr.2021.01.037 bezahl https://doi.org/10.1016/j.asr.2021.01.037 Fachbereich Luft- und Raumfahrttechnik OPUS4-9729 Wissenschaftlicher Artikel Hein, Andreas M., ; Eubanks, T. Marshall, ; Lingam, Manasvi, ; Hibberd, Adam, ; Fries, Dan, ; Schneider, Jean, ; Kervella, Pierre, ; Kennedy, Robert, ; Perakis, Nikolaos, ; Dachwald, Bernd, dachwald@fh-aachen.de Interstellar now! Missions to explore nearby interstellar objects The recently discovered first hyperbolic objects passing through the Solar System, 1I/'Oumuamua and 2I/Borisov, have raised the question about near term missions to Interstellar Objects. In situ spacecraft exploration of these objects will allow the direct determination of both their structure and their chemical and isotopic composition, enabling an entirely new way of studying small bodies from outside our solar system. In this paper, we map various Interstellar Object classes to mission types, demonstrating that missions to a range of Interstellar Object classes are feasible, using existing or near-term technology. We describe flyby, rendezvous and sample return missions to interstellar objects, showing various ways to explore these bodies characterizing their surface, dynamics, structure and composition. Their direct exploration will constrain their formation and history, situating them within the dynamical and chemical evolution of the Galaxy. These mission types also provide the opportunity to explore solar system bodies and perform measurements in the far outer solar system. Amsterdam Elsevier 2022 12 Advances in Space Research 69 1 402 414 10.1016/j.asr.2021.06.052 bezahl https://doi.org/10.1016/j.asr.2021.06.052 Fachbereich Luft- und Raumfahrttechnik OPUS4-9730 Konferenzveröffentlichung Grundmann, Jan Thimo, ; Bauer, Waldemar, ; Boden, Ralf, ; Ceriotti, Matteo, ; Chand, Suditi, ; Cordero, Federico, ; Dachwald, Bernd, dachwald@fh-aachen.de; Dumont, Etienne, ; Grimm, Christian D., ; Heiligers, Jeannette, ; Herčík, David, ; Hérique, Alain, ; Ho, Tra-Mi, ; Jahnke, Rico, ; Kofman, Wlodek, ; Lange, Caroline, ; Lichtenheldt, Roy, ; McInnes, Colin, ; Meß, Jan-Gerd, ; Mikschl, Tobias, ; Mikulz, Eugen, ; Montenegro, Sergio, ; Moore, Iain, ; Pelivan, Ivanka, ; Peloni, Alessandro, ; Plettemeier, Dirk, ; Quantius, Dominik, ; Reershemius, Siebo, ; Renger, Thomas, ; Riemann, Johannes, ; Rogez, Yves, ; Ruffer, Michael, ; Sasaki, Kaname, ; Schmitz, Nicole, ; Seboldt, Wolfgang, ; Seefeldt, Patric, ; Spietz, Peter, ; Spröwitz, Tom, ; Sznajder, Maciej, ; Tóth, Norbert, ; Vergaaij, Merel, ; Viavattene, Giulia, ; Wejmo, Elisabet, ; Wiedemann, Carsten, ; Wolff, Friederike, ; Ziach, Christian, 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 2019 6 70th International Astronautical Congress (IAC) 9781713814856 70th International Astronautical Congress (IAC), Washington D.C., United States, 21-25 October 2019 1 7 weltweit https://eprints.gla.ac.uk/202033/ Fachbereich Luft- und Raumfahrttechnik OPUS4-9959 Wissenschaftlicher Artikel Loeb, Horst Wolfgang, ; Schartner, Karl-Heinz, ; Dachwald, Bernd, Dachwald@fh-aachen.de; Ohndorf, Andreas, ; Seboldt, Wolfgang, Interstellar heliopause probe 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 traveling 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 European Space Agency (ESA). Two propulsion options for the mission have been proposed and discussed so far: the solar sail propulsion and the ballistic/radioisotope-electric propulsion (REP). As a further alternative, we here investigate a combination of solar-electric propulsion (SEP) and REP. The SEP stage consists of six 22-cms 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 at begin of mission (BOM) is provided by a lightweight solar array. Moskau Moskauer Staatliches Luftfahrtinstitut (МАИ) 2012 0 Труды МАИ 60 2 2 weltweit https://trudymai.ru/eng/published.php?ID=35089&referer=https%3A%2F%2Fwww.google.com%2F Fachbereich Luft- und Raumfahrttechnik OPUS4-9961 Konferenzveröffentlichung Ohndorf, Andreas, ; Dachwald, Bernd, Dachwald@fh-aachen.de; Seboldt, Wolfgang, ; Schartner, Karl-Heinz, Flight times to the heliopause using a combination of solar and radioisotope electric propulsion We investigate the interplanetary flight of a low-thrust space probe to the heliopause,located at a distance of about 200 AU from the Sun. Our goal was to reach this distance within the 25 years postulated by ESA for such a mission (which is less ambitious than the 15-year goal set by NASA). Contrary to solar sail concepts and combinations of allistic and electrically propelled flight legs, we have investigated whether the set flight time limit could also be kept with a combination of solar-electric propulsion and a second, RTG-powered upper stage. The used ion engine type was the RIT-22 for the first stage and the RIT-10 for the second stage. Trajectory optimization was carried out with the low-thrust optimization program InTrance, which implements the method of Evolutionary Neurocontrol,using Artificial Neural Networks for spacecraft steering and Evolutionary Algorithms to optimize the Neural Networks' parameter set. Based on a parameter space study, in which the number of thrust units, the unit's specific impulse, and the relative size of the solar power generator were varied, we have chosen one configuration as reference. The transfer time of this reference configuration was 29.6 years and the fastest one, which is technically more challenging, still required 28.3 years. As all flight times of this parameter study were longer than 25 years, we further shortened the transfer time by applying a launcher-provided hyperbolic excess energy up to 49 km2/s2. The resulting minimal flight time for the reference configuration was then 27.8 years. The following, more precise optimization to a launch with the European Ariane 5 ECA rocket reduced the transfer time to 27.5 years. This is the fastest mission design of our study that is flexible enough to allow a launch every year. The inclusion of a fly-by at Jupiter finally resulted in a flight time of 23.8 years,which is below the set transfer-time limit. However, compared to the 27.5-year transfer,this mission design has a significantly reduced launch window and mission flexibility if the escape direction is restricted to the heliosphere's "nose". 2011 12 32nd International Electric Propulsion Conference IEPC-2011-051 32nd International Electric Propulsion Conference,September 11-15, 2011 Wiesbaden, Germany 1 12 weltweit https://elib.dlr.de/70898/1/IEPC-2011-051.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-9963 Konferenzveröffentlichung Borggräfe, Andreas, ; Dachwald, Bernd, Dachwald@fh-aachen.de Mission performance evaluation for solar sails using a refined SRP force model with variable optical coefficients Solar sails provide ignificant advantages over other low-thrust propulsion systems because they produce thrust by the momentum exchange from solar radiation pressure (SRP) and thus do not consume any propellant.The force exerted on a very thin sail foil basically depends on the light incidence angle. Several analytical SRP force models that describe the SRP force acting on the sail have been established since the 1970s. All the widely used models use constant optical force coefficients of the reflecting sail material. In 2006,MENGALI et al. proposed a refined SRP force model that takes into account the dependancy of the force coefficients on the light incident angle,the sail's distance from the sun (and thus the sail emperature) and the surface roughness of the sail material [1]. In this paper, the refined SRP force model is compared to the previous ones in order to identify the potential impact of the new model on the predicted capabilities of solar sails in performing low-cost interplanetary space missions. All force models have been implemented within InTrance, a global low-thrust trajectory optimization software utilizing evolutionary neurocontrol [2]. Two interplanetary rendezvous missions, to Mercury and the near-Earth asteroid 1996FG3, are investigated. Two solar sail performances in terms of characteristic acceleration are examined for both scenarios, 0.2 mm/s2 and 0.5 mm/s2, termed "low" and "medium" sail performance. In case of the refined SRP model, three different values of surface roughness are chosen, h = 0 nm, 10 nm and 25 nm. The results show that the refined SRP force model yields shorter transfer times than the standard model. 2010 6 2nd International Symposium on Solar Sailing 2nd International Symposium on Solar Sailing, ISSS 2010, 2010-07-20 - 2010-07-22. New York City College of Technology of the City University of New York, USA 1 6 Campus https://strathprints.strath.ac.uk/48735/1/Borggrafe_A_Dachwald_B_Pure_Mission_performance_evaluation_for_solar_sails_using_a_refined_SRP_force_model_with_variable_optical_coefficients_Jul_2010.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-9968 Konferenzveröffentlichung Schartner, Karl-Heinz, ; Loeb, H. W., ; Dachwald, Bernd, Dachwald@fh-aachen.de; Ohndorf, Andreas, Perspectives of electric propulsion for outer planetary and deep space missions Solar-electric propulsion (SEP) is superior with respect to payload capacity, flight time and flexible launch window to the conventional interplanetary transfer method using chemical propulsion combined with gravity assists. This fact results from the large exhaust velocities of electric low-thrust propulsion and is favourable also for missions to the giant planets, Kuiper-belt objects and even for a heliopause probe (IHP) as shown in three studies by the authors funded by DLR. They dealt with a lander for Europa and a sample return mission from a mainbelt asteroid [1], with the TANDEM mission [2]; the third recent one investigates electric propulsion for the transfer to the edge of the solar system. All studies are based on triple-junction solar arrays, on rf-ion thrusters of the qualified RIT-22 type and they use the intelligent trajectory optimization program InTrance [3]. 2009 1 European Planetary Science Congress 2009 European Planetary Science Congress 2009, 13-18 September, Potsdam, Germany 416 416 https://www.researchgate.net/publication/253512384_Perspectives_of_Electric_Propulsion_for_Outer_Planetary_and_Deep_Space_Missions Fachbereich Luft- und Raumfahrttechnik OPUS4-9969 Konferenzveröffentlichung Spurmann, Jörn, ; Ohndorf, Andreas, ; Dachwald, Bernd, Dachwald@fh-aachen.de; Seboldt, Wolfgang, ; Löb, Horst, ; Schartner, Karl-Heinz, Interplanetary trajectory optimization for a sep mission to Saturn The recently proposed NASA and ESA missions to Saturn and Jupiter pose difficult tasks to mission designers because chemical propulsion scenarios are not capable of transferring heavy spacecraft into the outer solar system without the use of gravity assists. Thus our developed mission scenario based on the joint NASA/ESA Titan Saturn System Mission baselines solar electric propulsion to improve mission flexibility and transfer time. For the calculation of near-globally optimal low-thrust trajectories, we have used a method called Evolutionary Neurocontrol, which is implemented in the low-thrust trajectory optimization software InTrance. The studied solar electric propulsion scenario covers trajectory optimization of the interplanetary transfer including variations of the spacecraft's thrust level, the thrust unit's specific impulse and the solar power generator power level. Additionally developed software extensions enabled trajectory optimization with launcher-provided hyperbolic excess energy, a complex solar power generator model and a variable specific impulse ion engine model. For the investigated mission scenario, Evolutionary Neurocontrol yields good optimization results, which also hold valid for the more elaborate spacecraft models. Compared to Cassini/Huygens, the best found solutions have faster transfer times and a higher mission flexibility in general. 2009 15 60th International Astronautical Congress 2009 9781615679089 60th International Astronautical Congress 2009 (IAC 2009) Held 12-16 October 2009, Daejeon, Republic of Korea. 5234 5248 bezahl https://elib.dlr.de/63541/ Fachbereich Luft- und Raumfahrttechnik OPUS4-9970 Konferenzveröffentlichung Loeb, Horst Wolfgang, ; Schartner, Karl-Heinz, ; Dachwald, Bernd, Dachwald@fh-aachen.de; Seboldt, Wolfgang, SEP-Sample return from a main belt asteroid By DLR-contact, sample return missions to the large main-belt asteroid "19, Fortuna" have been studied. The mission scenario has been based on three ion thrusters of the RIT-22 model, which is presently under space qualification, and on solar arrays equipped with triple-junction GaAs solar cells. After having designed the spacecraft, the orbit-to-orbit trajectories for both, a one-way SEP mission with a chemical sample return and an all-SEP return mission, have been optimized using a combination of artificial neural networks with evolutionary algorithms. Additionally, body-to-body trajectories have been investigated within a launch period between 2012 and 2015. For orbit-to-orbit calculation, the launch masses of the hybrid mission and of the all-SEP mission resulted in 2.05 tons and 1.56 tons, respectively, including a scientific payload of 246 kg. For the related transfer durations 4.14 yrs and 4.62 yrs were obtained. Finally, a comparison between the mission scenarios based on SEP and on NEP have been carried out favouring clearly SEP. 2007 11 30th International Electric Propulsion Conference 30th International Electric Propulsion Conference, Florence, Italy September 17-20, 2007 1 11 weltweit http://electricrocket.org/IEPC/IEPC-2007-048.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-9971 Konferenzveröffentlichung Dachwald, Bernd, Dachwald@fh-aachen.de; Mengali, Giovanni, ; Quarta, Alessandro A, ; Macdonald, Malcolm, ; McInnes, Colin R, Optical solar sail degradation modelling We propose a simple parametric OSSD model that describes the variation of the sail film's optical coefficients with time, depending on the sail film's environmental history, i.e., the radiation dose. The primary intention of our model is not to describe the exact behavior of specific film-coating combinations in the real space environment, but to provide a more general parametric framework for describing the general optical degradation behavior of solar sails. 2007 27 1st International Symposium on Solar Sailing 1st International Symposium on Solar Sailing 27-29 June 2007, Herrsching, Germany 1 27 http://www.isss.spacesailing.net/ Fachbereich Luft- und Raumfahrttechnik OPUS4-9972 Wissenschaftlicher Artikel Dachwald, Bernd, Dachwald@fh-aachen.de Optimization of very-low-thrust trajectories using evolutionary neurocontrol Searching optimal interplanetary trajectories for low-thrust spacecraft is usually a difficult and time-consuming task that involves much experience and expert knowledge in astrodynamics and optimal control theory. This is because the convergence behavior of traditional local optimizers, which are based on numerical optimal control methods, depends on an adequate initial guess, which is often hard to find, especially for very-low-thrust trajectories that necessitate many revolutions around the sun. The obtained solutions are typically close to the initial guess that is rarely close to the (unknown) global optimum. Within this paper, trajectory optimization problems are attacked from the perspective of artificial intelligence and machine learning. Inspired by natural archetypes, a smart global method for low-thrust trajectory optimization is proposed that fuses artificial neural networks and evolutionary algorithms into so-called evolutionary neurocontrollers. This novel method runs without an initial guess and does not require the attendance of an expert in astrodynamics and optimal control theory. This paper details how evolutionary neurocontrol works and how it could be implemented. The performance of the method is assessed for three different interplanetary missions with a thrust to mass ratio <0.15mN/kg (solar sail and nuclear electric). Amsterdam [u.a.] Elsevier 2005 10 Acta Astronautica 57 1879-2030 2-8 175 185 bezahl https://www.sciencedirect.com/science/article/abs/pii/S0094576505000627?via%3Dihub Fachbereich Luft- und Raumfahrttechnik OPUS4-9973 Konferenzveröffentlichung Schoutetens, Frederic, ; Dachwald, Bernd, Dachwald@fh-aachen.de; Heiligers, Jeannette, Optimisation of photon-sail trajectories in the alpha-centauri system using evolutionary neurocontrol With the increased interest for interstellar exploration after the discovery of exoplanets and the proposal by Breakthrough Starshot, this paper investigates the optimisation of photon-sail trajectories in Alpha Centauri. The prime objective is to find the optimal steering strategy for a photonic sail to get captured around one of the stars after a minimum-time transfer from Earth. By extending the idea of the Breakthrough Starshot project with a deceleration phase upon arrival, the mission's scientific yield will be increased. As a secondary objective, transfer trajectories between the stars and orbit-raising manoeuvres to explore the habitable zones of the stars are investigated. All trajectories are optimised for minimum time of flight using the trajectory optimisation software InTrance. Depending on the sail technology, interstellar travel times of 77.6-18,790 years can be achieved, which presents an average improvement of 30% with respect to previous work. Still, significant technological development is required to reach and be captured in the Alpha-Centauri system in less than a century. Therefore, a fly-through mission arguably remains the only option for a first exploratory mission to Alpha Centauri, but the enticing results obtained in this work provide perspective for future long-residence missions to our closest neighbouring star system. 2021 15 8th ICATT (International Conference on Astrodynamics Tools and Techniques) 23 - 25 June 2021, Virtual 8th ICATT (International Conference on Astrodynamics Tools and Techniques) 23 - 25 June 2021, Virtual 1 15 weltweit https://pure.tudelft.nl/ws/portalfiles/portal/104875986/2021_Schoutetens_Dachwald_Heiligers_Optimisation_trajectories_Alpha_Centauri.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-9975 Konferenzveröffentlichung Seefeldt, Patric, ; Bauer, Waldemar, ; Dachwald, Bernd, Dachwald@fh-aachen.de; Grundmann, Jan Thimo, ; Straubel, Marco, ; Sznajder, Maciej, ; Tóth, Norbert, ; Zander, Martin E., Large lightweight deployable structures for planetary defence: solar sail propulsion, solar concentrator payloads, large-scale photovoltaic power 2015 24 4th IAA Planetary Defense Conference - PDC 2015, 13-17 April 2015, Frascati, Roma, Italy IAA-PDC-15-P-20 weltweit https://iaaspace.org/wp-content/uploads/iaa/Scientific%20Activity/conf/pdc2015/IAA-PDC-15-P-20pa.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-9977 Konferenzveröffentlichung Dachwald, Bernd, Dachwald@fh-aachen.de Radiation pressure force model for an ideal laser-enhanced solar sail The concept of a laser-enhanced solar sail is introduced and the radiation pressure force model for an ideal laser-enhanced solar sail is derived. A laser-enhanced solar sail is a "traditional" solar sail that is, however, not solely propelled by solar radiation, but additionally by a laser beam that illuminates the sail. The additional laser radiation pressure increases the sail's propulsive force and can give, depending on the location of the laser source, more control authority over the direction of the solar sail's propulsive force vector. This way, laser-enhanced solar sails may augment already existing solar sail mission concepts and make novel mission concepts feasible. 2017 5 4th International Symposium on Solar Sailing 4th International Symposium on Solar Sailing 17-20 January 2017, Kyōto, Japan 1 5 weltweit https://www.jsforum.or.jp/ISSS2017/papers/paper/17021_Paper_Bernd%20Dachwald.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-9948 Konferenzveröffentlichung Dachwald, Bernd, dachwald@fh-aachen.de; Kahle, Ralph, ; Wie, Bong, Head-on impact deflection of NEAs: a case study for 99942 Apophis Near-Earth asteroid (NEA) 99942 Apophis provides a typical example for the evolution of asteroid orbits that lead to Earth-impacts after a close Earth-encounter that results in a resonant return. Apophis will have a close Earth-encounter in 2029 with potential very close subsequent Earth-encounters (or even an impact) in 2036 or later, depending on whether it passes through one of several less than 1 km-sized gravitational keyholes during its 2029-encounter. A pre-2029 kinetic impact is a very favorable option to nudge the asteroid out of a keyhole. The highest impact velocity and thus deflection can be achieved from a trajectory that is retrograde to Apophis orbit. With a chemical or electric propulsion system, however, many gravity assists and thus a long time is required to achieve this. We show in this paper that the solar sail might be the better propulsion system for such a mission: a solar sail Kinetic Energy Impactor (KEI) spacecraft could impact Apophis from a retrograde trajectory with a very high relative velocity (75-80 km/s) during one of its perihelion passages. The spacecraft consists of a 160 m × 160 m, 168 kg solar sail assembly and a 150 kg impactor. Although conventional spacecraft can also achieve the required minimum deflection of 1 km for this approx. 320 m-sized object from a prograde trajectory, our solar sail KEI concept also allows the deflection of larger objects. For a launch in 2020, we also show that, even after Apophis has flown through one of the gravitational keyholes in 2029, the solar sail KEI concept is still feasible to prevent Apophis from impacting the Earth, but many KEIs would be required for consecutive impacts to increase the total Earth-miss distance to a safe value 2007 11 Planetary Defense Conference 2007 Planetary Defense Conference 2007, Wahington D.C., USA, 05-08 March 2007 1 12 Weltweit http://spacesailing.net/paper/200703_washington_dachwaldkahlewie.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-9949 Konferenzveröffentlichung Grundmann, Jan Thimo, ; Boden, Ralf, ; Ceriotti, Matteo, ; Dachwald, Bernd, dachwald@fh-aachen.de; Dumont, Etienne, ; Grimm, Christian D., ; Lange, Caroline, ; Lichtenheldt, Roy, ; Pelivan, Ivanka, ; Peloni, Alessandro, ; Riemann, Johannes, ; Spröwitz, Tom, ; Tardivel, Simon, Soil to sail-asteroid landers on near-term sailcraft as an evolution of the GOSSAMER small spacecraft solar sail concept for in-situ characterization 2017 30 Seiten 5th IAA Planetary Defense Conference 5th IAA Planetary Defense Conference - PDC 2017 15-19 May 2017, Tokyo, Japan weltweit https://elib.dlr.de/118805/1/IAA-PDC-17-05-19ea.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-9951 Teil eines Buches Dachwald, Bernd, dachwald@fh-aachen.de Solar sail dynamics and control Solar sails are large and lightweight reflective structures that are propelled by solar radiation pressure. This chapter covers their orbital and attitude dynamics and control. First, the advantages and limitations of solar sails are discussed and their history and development status is outlined. Because the dynamics of solar sails is governed by the (thermo-)optical properties of the sail film, the basic solar radiation pressure force models have to be described and compared before parameters to measure solar sail performance can be defined. The next part covers the orbital dynamics of solar sails for heliocentric motion, planetocentric motion, and motion at Lagrangian equilibrium points. Afterwards, some advanced solar radiation pressure force models are described, which allow to quantify the thrust force on solar sails of arbitrary shape, the effects of temperature, of light incidence angle, of surface roughness, and the effects of optical degradation of the sail film in the space environment. The orbital motion of a solar sail is strongly coupled to its rotational motion, so that the attitude control of these soft and flexible structures is very challenging, especially for planetocentric orbits that require fast attitude maneuvers. Finally, some potential attitude control methods are sketched and selection criteria are given. Hoboken Wiley 2010 Encyclopedia of Aerospace Engineering 10.1002/9780470686652.eae292 bezahl https://doi.org/10.1002/9780470686652.eae292 Fachbereich Luft- und Raumfahrttechnik OPUS4-9952 Konferenzveröffentlichung Seboldt, Wolfgang, ; Dachwald, Bernd, dachwald@fh-aachen.de Solar sails for near-term advanced scientific deep space missions Solar sails are propelled in space by reflecting solar photons off large mirroring surfaces, thereby transforming the momentum of the photons into a propulsive force. This innovative concept for low-thrust space propulsion works without any propellant and thus provides a wide range of opportunities for highenergy low-cost missions. Offering an efficient way of propulsion, solar sailcraft could close a gap in transportation options for highly demanding exploration missions within our solar system and even beyond. On December 17th, 1999, a significant step was made towards the realization of this technology: a lightweight solar sail structure with an area of 20 m × 20 m was successfully deployed on ground in a large facility at the German Aerospace Center (DLR) at Cologne. The deployment from a package of 60 cm × 60 cm × 65 cm with a total mass of less than 35 kg was achieved using four extremely light-weight carbon fiber reinforced plastics (CFRP) booms with a specific mass of 100 g/m. The paper briefly reviews the basic principles of solar sails as well as the technical concept and its realization in the ground demonstration experiment, performed in close cooperation between DLR and ESA. Next possible steps are outlined. They could comprise the in-orbit demonstration of the sail deployment on the upper stage of a low-cost rocket and the verification of the propulsion concept by an autonomous and free flying solar sail in the frame of a scientific mission. It is expected that the present design could be extended to sail sizes of about (40 m)2 up to even (70 m)2 without significant mass penalty. With these areas, the maximum achievable thrust at 1 AU would range between 10 and 40 mN - comparable to some electric thrusters. Such prototype sails with a mass between 50 and 150 kg plus a micro-spacecraft of 50 to 250 kg would have a maximum acceleration in the order of 0.1 mm/s2 at 1 AU, corresponding to a maximum ∆V-capability of about 3 km/s per year. Two near/medium-term mission examples to a near-Earth asteroid (NEA) will be discussed: a rendezvous mission and a sample return mission. 2003 14 Seiten Proceedings of the 8th International Workshop on Combustion and Propulsion Proceedings of the 8th International Workshop on Combustion and Propulsion. Pozzuoli, Italy, 16 - 21 June 2002. weltweit http://spacesailing.net/paper/200207_Pozzuoli_SeboldtDachwald.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-9953 Konferenzveröffentlichung Dachwald, Bernd, dachwald@fh-aachen.de; Seboldt, Wolfgang, ; Häusler, Bernd, Performance requirements for near-term interplanetary solar sailcraft missions Solar sailcraft provide a wide range of opportunities for high-energy low-cost missions. To date, most mission studies require a rather demanding performance that will not be realized by solar sailcraft of the first generation. However, even with solar sailcraft of moderate performance, scientifically relevant missions are feasible. This is demonstrated with a Near Earth Asteroid sample return mission and various planetary rendezvous missions. 2002 9 Seiten 6th International AAAF Symposium on Space Propulsion: Propulsion for Space Transportation of the XXIst Century 6th International AAAF Symposium on Space Propulsion: Propulsion for Space Transportation of the XXIst Century, Versailles, France, 14-16 May 2002 weltweit http://www.spacesailing.net/paper/200205_Versailles_DachwaldSeboldtHaeusler.pdf Fachbereich Luft- und Raumfahrttechnik OPUS4-9927 Wissenschaftlicher Artikel Peloni, Alessandro, ; Ceriotti, Matteo, ; Dachwald, Bernd, dachwald@fh-aachen.de Solar-sail trajectory design for a multiple near-earth-asteroid rendezvous mission The scientific interest for near-Earth asteroids as well as the interest in potentially hazardous asteroids from the perspective of planetary defense led the space community to focus on near-Earth asteroid mission studies. A multiple near-Earth asteroid rendezvous mission with close-up observations of several objects can help to improve the characterization of these asteroids. This work explores the design of a solar-sail spacecraft for such a mission, focusing on the search of possible sequences of encounters and the trajectory optimization. This is done in two sequential steps: a sequence search by means of a simplified trajectory model and a set of heuristic rules based on astrodynamics, and a subsequent optimization phase. A shape-based approach for solar sailing has been developed and is used for the first phase. The effectiveness of the proposed approach is demonstrated through a fully optimized multiple near-Earth asteroid rendezvous mission. The results show that it is possible to visit five near-Earth asteroids within 10 years with near-term solar-sail technology. Reston, Va. AIAA 2016 12 Journal of Guidance, Control, and Dynamics 39 12 2712 2724 10.2514/1.G000470 bezahl https://doi.org/10.2514/1.G000470 Fachbereich Luft- und Raumfahrttechnik OPUS4-9929 Konferenzveröffentlichung Dachwald, Bernd, dachwald@fh-aachen.de Solar sail performance requirements for missions to the outer solar system and beyond Solar sails enable missions to the outer solar system and beyond, although the solar radiation pressure decreases with the square of solar distance. For such missions, the solar sail may gain a large amount of energy by first making one or more close approaches to the sun. Within this paper, optimal trajectories for solar sail missions to the outer planets and into near interstellar space (200 AU) are presented. Thereby, it is shown that even near/medium-term solar sails with relatively moderate performance allow reasonable transfer times to the boundaries of the solar system. 2004 8 55th International Astronautical Congress 2004 55th International Astronautical Congress 2004 - Vancouver, Canada 1 9 10.2514/6.IAC-04-S.P.11 weltweit https://doi.org/10.2514/6.IAC-04-S.P.11 Fachbereich Luft- und Raumfahrttechnik OPUS4-8980 Konferenzveröffentlichung Waldmann, Christoph, ; Vera, Jean-Pierre de, ; Dachwald, Bernd, dachwald@fh-aachen.de; Strasdeit, Henry, ; Sohl, Frank, ; Hanff, Hendrik, ; Kowalski, Julia, ; Heinen, Dirk, ; Macht, Sabine, ; Bestmann, Ulf, ; Meckel, Sebastian, ; Hildebrandt, Marc, ; Funke, Oliver, ; Gehrt, Jan-Jöran, Search for life in ice-covered oceans and lakes beyond Earth The quest for life on other planets is closely connected with the search for water in liquid state. Recent discoveries of deep oceans on icy moons like Europa and Enceladus have spurred an intensive discussion about how these waters can be accessed. The challenge of this endeavor lies in the unforeseeable requirements on instrumental characteristics both with respect to the scientific and technical methods. The TRIPLE/nanoAUV initiative is aiming at developing a mission concept for exploring exo-oceans and demonstrating the achievements in an earth-analogue context, exploring the ocean under the ice shield of Antarctica and lakes like Dome-C on the Antarctic continent. 2018 2018 IEEE/OES Autonomous Underwater Vehicle Workshop, Proceedings November 2018, Article number 8729761 10.1109/AUV.2018.8729761 campus http://dx.doi.org/10.1109/AUV.2018.8729761 Fachbereich Luft- und Raumfahrttechnik OPUS4-9001 Konferenzveröffentlichung Grundmann, Jan Thimo, ; Bauer, Wlademar, ; Borchers, Kai, ; Dumont, Etienne, ; Grimm, Christian D., ; Ho, Tra-Mi, ; Jahnke, Rico, ; Koch, Aaron D., ; Lange, Caroline, ; Maiwald, Volker, ; Meß, Jan-Gerd, ; Mikulz, Eugen, ; Quantius, Dominik, ; Reershemius, Siebo, ; Renger, Thomas, ; Sasaki, Kaname, ; Seefeldt, Patric, ; Spietz, Peter, ; Spröwitz, Tom, ; Sznajder, Maciej, ; Toth, Norbert, ; Ceriotti, Matteo, ; McInnes, Colin, ; Peloni, Alessandro, ; Biele, Jens, ; Krause, Christian, ; Dachwald, Bernd, dachwald@fh-aachen.de; Hercik, David, ; Lichtenheldt, Roy, ; Wolff, Friederike, ; Koncz, Alexander, ; Pelivan, Ivanka, ; Schmitz, Nicole, ; Boden, Ralf, ; Riemann, Johannes, ; Seboldt, Wolfgang, ; Wejmo, Elisabet, ; Ziach, Christian, ; Mikschl, Tobias, ; Montenegro, Sergio, ; Ruffer, Michael, ; Cordero, Federico, ; Tardivel, Simon, Solar sails for planetary defense & high-energy missions 20 years after the successful ground deployment test of a (20 m) 2 solar sail at DLR Cologne, and in the light of the upcoming U.S. NEAscout mission, we provide an overview of the progress made since in our mission and hardware design studies as well as the hardware built in the course of our solar sail technology development. We outline the most likely and most efficient routes to develop solar sails for useful missions in science and applications, based on our developed `now-term' and near-term hardware as well as the many practical and managerial lessons learned from the DLR-ESTEC Gossamer Roadmap. Mission types directly applicable to planetary defense include single and Multiple NEA Rendezvous ((M)NR) for precursor, monitoring and follow-up scenarios as well as sail-propelled head-on retrograde kinetic impactors (RKI) for mitigation. Other mission types such as the Displaced L1 (DL1) space weather advance warning and monitoring or Solar Polar Orbiter (SPO) types demonstrate the capability of near-term solar sails to achieve asteroid rendezvous in any kind of orbit, from Earth-coorbital to extremely inclined and even retrograde orbits. Some of these mission types such as SPO, (M)NR and RKI include separable payloads. For one-way access to the asteroid surface, nanolanders like MASCOT are an ideal match for solar sails in micro-spacecraft format, i.e. in launch configurations compatible with ESPA and ASAP secondary payload platforms. Larger landers similar to the JAXA-DLR study of a Jupiter Trojan asteroid lander for the OKEANOS mission can shuttle from the sail to the asteroids visited and enable multiple NEA sample-return missions. The high impact velocities and re-try capability achieved by the RKI mission type on a final orbit identical to the target asteroid's but retrograde to its motion enables small spacecraft size impactors to carry sufficient kinetic energy for deflection. 2019 20 IEEE Aerospace Conference Proceedings AERO 2019; Big Sky; United States; 2 March 2019 through 9 March 2019 1 21 10.1109/AERO.2019.8741900 https://doi.org/10.1109/AERO.2019.8741900 Fachbereich Luft- und Raumfahrttechnik OPUS4-9335 Wissenschaftlicher Artikel Dachwald, Bernd, dachwald@fh-aachen.de; Ulamec, Stephan, ; Postberg, Frank, ; Sohl, Frank, ; Vera, Jean-Pierre de, ; Christoph, Waldmann, ; Lorenz, Ralph D., ; Hellard, Hugo, ; Biele, Jens, ; Rettberg, Petra, Key technologies and instrumentation for subsurface exploration of ocean worlds In this chapter, the key technologies and the instrumentation required for the subsurface exploration of ocean worlds are discussed. The focus is laid on Jupiter's moon Europa and Saturn's moon Enceladus because they have the highest potential for such missions in the near future. The exploration of their oceans requires landing on the surface, penetrating the thick ice shell with an ice-penetrating probe, and probably diving with an underwater vehicle through dozens of kilometers of water to the ocean floor, to have the chance to find life, if it exists. Technologically, such missions are extremely challenging. The required key technologies include power generation, communications, pressure resistance, radiation hardness, corrosion protection, navigation, miniaturization, autonomy, and sterilization and cleaning. Simpler mission concepts involve impactors and penetrators or - in the case of Enceladus - plume-fly-through missions. Dordrecht Springer 2020 45 Space Science Reviews 216 Corresponding author: Bernd Dachwald Art. 83 10.1007/s11214-020-00707-5 weltweit https://doi.org/10.1007/s11214-020-00707-5 Fachbereich Luft- und Raumfahrttechnik OPUS4-9361 Wissenschaftlicher Artikel Hein, Andreas M., ; Eubanks, T. Marshall, ; Hibberd, Adam, ; Fries, Dan, ; Schneider, Jean, ; Lingam, Manasvi, ; Kennedy, Robert, ; Perakis, Nikolaos, ; Dachwald, Bernd, dachwald@fh-aachen.de; Kervella, Pierre, Interstellar Now! Missions to and sample returns from nearby interstellar objects The recently discovered first high velocity hyperbolic objects passing through the Solar System, 1I/'Oumuamua and 2I/Borisov, have raised the question about near term missions to Interstellar Objects. In situ spacecraft exploration of these objects will allow the direct determination of both their structure and their chemical and isotopic composition, enabling an entirely new way of studying small bodies from outside our solar system. In this paper, we map various Interstellar Object classes to mission types, demonstrating that missions to a range of Interstellar Object classes are feasible, using existing or near-term technology. We describe flyby, rendezvous and sample return missions to interstellar objects, showing various ways to explore these bodies characterizing their surface, dynamics, structure and composition. Interstellar objects likely formed very far from the solar system in both time and space; their direct exploration will constrain their formation and history, situating them within the dynamical and chemical evolution of the Galaxy. These mission types also provide the opportunity to explore solar system bodies and perform measurements in the far outer solar system. Amsterdam Elsevier 2020 8 1 8 weltweit https://arxiv.org/abs/2008.07647 Fachbereich Luft- und Raumfahrttechnik OPUS4-11057 Konferenzveröffentlichung Gehler, M., ; Ober-Blöbaum, S., ; Dachwald, Bernd, Dachwald@fh-aachen.de Application of discrete mechanics and optimal control to spacecraft in non-keplerian motion around small solar system bodies Prolonged operations close to small solar system bodies require a sophisticated control logic to minimize propellant mass and maximize operational efficiency. A control logic based on Discrete Mechanics and Optimal Control (DMOC) is proposed and applied to both conventionally propelled and solar sail spacecraft operating at an arbitrarily shaped asteroid in the class of Itokawa. As an example, stand-off inertial hovering is considered, recently identified as a challenging part of the Marco Polo mission. The approach is easily extended to stand-off orbits. We show that DMOC is applicable to spacecraft control at small objects, in particular with regard to the fact that the changes in gravity are exploited by the algorithm to optimally control the spacecraft position. Furthermore, we provide some remarks on promising developments. Amsterdam Elsevier 2009 11 Procceedings of the 60th International Astronautical Congress 978-161567908-9 60th International Astronautical Congress 2009, IAC 2009; Daejeon; South Korea; 12 October 2009 through 16 October 2009 1360 1371 bezahl https://www.scopus.com/record/display.uri?eid=2-s2.0-77953551203&origin=inward&txGid=55a9d77f018557e6d78a7421419a8393 Fachbereich Luft- und Raumfahrttechnik OPUS4-11058 Konferenzveröffentlichung Dachwald, Bernd, Dachwald@fh-aachen.de; Wurm, P., Design concept and modeling of an advanced solar photon thruster The so-called "compound solar sail", also known as "Solar Photon Thruster" (SPT), holds the potential of providing significant performance advantages over the flat solar sail. Previous SPT design concepts, however, do not consider shadowing effects and multiple reflections of highly concentrated solar radiation that would inevitably destroy the gossamer sail film. In this paper, we propose a novel advanced SPT (ASPT) design concept that does not suffer from these oversimplifications. We present the equations that describe the thrust force acting on such a sail system and compare its performance with respect to the conventional flat solar sail. San Diego, Calif. American Astronautical Society 2009 17 Advances in the Astronautical Sciences 978-087703554-1 19th AAS/AIAA Space Flight Mechanics Meeting; Savannah, GA; United States; 8 February 2009 through 12 February 2009 723 740 bezahl https://www.scopus.com/record/display.uri?eid=2-s2.0-80053408846&origin=inward&txGid=c71a812af6b448da0e0cb316e77aae9c Fachbereich Luft- und Raumfahrttechnik OPUS4-11059 Teil eines Buches Dachwald, Bernd, Dachwald@fh-aachen.de Knopf, George K.; Otani, Yukitoshi Light propulsion systems for spacecraft Boca Raton CRC Press 2017 21 Optical nano and micro actuator technology 9781315217628 (eBook) 577 598 bezahl https://doi.org/10.1201/b13892 Fachbereich Luft- und Raumfahrttechnik OPUS4-11060 Konferenzveröffentlichung Dachwald, Bernd, Dachwald@fh-aachen.de; Wurm, P., Mission analysis for an advanced solar photon thruster The so-called "compound solar sail", also known as "Solar Photon Thruster" (SPT), is a solar sail design concept, for which the two basic functions of the solar sail, namely light collection and thrust direction, are uncoupled. In this paper, we introduce a novel SPT concept, termed the Advanced Solar Photon Thruster (ASPT). This model does not suffer from the simplified assumptions that have been made for the analysis of compound solar sails in previous studies. We present the equations that describe the force, which acts on the ASPT. After a detailed design analysis, the performance of the ASPT with respect to the conventional flat solar sail (FSS) is investigated for three interplanetary mission scenarios: An Earth-Venus rendezvous, where the solar sail has to spiral towards the Sun, an Earth-Mars rendezvous, where the solar sail has to spiral away from the Sun, and an Earth-NEA rendezvous (to near-Earth asteroid 1996FG3), where a large orbital eccentricity change is required. The investigated solar sails have realistic near-term characteristic accelerations between 0.1 and 0.2mm/s2. Our results show that a SPT is not superior to the flat solar sail unless very idealistic assumptions are made. Amsterdam Elsevier 2009 13 60th International Astronautical Congress 2009, IAC 2009 Vol. 8 978-161567908-9 60th International Astronautical Congress 2009, IAC 2009; Daejeon; South Korea; 12 October 2009 through 16 October 2009 6838 6851 bezahl https://www.scopus.com/record/display.uri?eid=2-s2.0-77953533204&origin=inward&txGid=c637e44976e432afea2a2e2f828900f6 Fachbereich Luft- und Raumfahrttechnik