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 OPUS4-10073 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 OPUS4-10095 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 OPUS4-10016 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 OPUS4-10034 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 OPUS4-9730 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 OPUS4-9001 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