TY  - CHAP
A1  - Voronkova, Eva B.
A1  - Bauer, Svetlana M.
A1  - Kotliar, Konstantin
T1  - Computer simulation of the cornea-scleral shell as applied to pressure-volume relationship in the human eye
T2  - 2014 International Conference on Computer Technologies in Physical and Engineering Applications :  ICCTPEA 2014 : proceedings : June 30 2014-July 4 2014, St. Petersburg
Y1  - 2014
SN  - 978-1-4799-5315-8
SP  - 204
EP  - 205
ER  - 
TY  - CHAP
A1  - Loeb, Horst Wolfgang
A1  - Schartner, Karl-Heinz
A1  - Dachwald, Bernd
A1  - Seboldt, Wolfgang
T1  - SEP-Sample return from a main belt asteroid
T2  - 30th International Electric Propulsion Conference
N2  - 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.
Y1  - 2007
SP  - 1
EP  - 11
ER  - 
TY  - CHAP
A1  - Dachwald, Bernd
A1  - Ohndorf, Andreas
A1  - Spurmann, J.
A1  - Loeb, H. W.
A1  - Schartner, Karl-Heinz
A1  - Seboldt, Wolfgang
T1  - Mission design for a SEP mission to saturn
T2  - 60th International Astronautical Congress 2009 (IAC 2009)
N2  - Within ESA's Cosmic Vision 2015-2025 plan, a mission to explore the Saturnian System, with special emphasis on its two moons Titan and Enceladus, was selected for study, termed TANDEM (Titan and Enceladus Mission). In this paper, we describe an optimized mission design for a TANDEM-derived solar electric propulsion (SEP) mission. We have chosen the SEP mission scenario for the interplanetary transfer of the TANDEM spacecraft because all feasible gravity assist sequences for a chemical transfer between 2015 and 2025 result in long flight times of about nine years. Our SEP system is based on the German RIT ion engine. For our optimized mission design, we have extensively explored the SEP parameter space (specific impulse, thrust level, power level) and have calculated an optimal interplanetary trajectory for each setting. In contrast to the original TANDEM mission concept, which intends to use two launch vehicles and an all-chemical transfer, our SEP mission design requires only a single Ariane 5 ECA launch for the same payload mass. Without gravity assist, it yields a faster and more flexible transfer with a fight time of less than seven years, and an increased payload ratio. Our mission design proves thereby the capability of SEP even for missions into the outer solar system.
Y1  - 2009
SN  - 978-1-61567-908-9
N1  - 12-16 October 2009, Daejeon, Republic of Korea.
PB  - Curran Associates, Inc.
CY  - Red Hook, NY
ER  - 
TY  - CHAP
A1  - Dachwald, Bernd
A1  - Wurm, P.
T1  - Design concept and modeling of an advanced solar photon thruster
T2  - Advances in the Astronautical Sciences
N2  - 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.
KW  - solar sails
Y1  - 2009
SN  - 978-087703554-1
SN  - 00653438
N1  - 19th AAS/AIAA Space Flight Mechanics Meeting; Savannah, GA; United States; 8 February 2009 through 12 February 2009
SP  - 723
EP  - 740
PB  - American Astronautical Society
CY  - San Diego, Calif.
ER  - 
TY  - CHAP
A1  - Grundmann, Jan Thimo
A1  - Biele, Jens
A1  - Dachwald, Bernd
A1  - Grimm, Christian D.
A1  - Lange, Caroline
A1  - Ulamec, Stephan
A1  - Ziach, Christian
A1  - Spröwitz, Tom
A1  - Ruffer, Michael
A1  - Seefeldt, Patric
A1  - Spietz, Peter
A1  - Toth, Norbert
A1  - Mimasu, Yuya
A1  - Rittweger, Andreas
A1  - Bibring, Jean-Pierre
A1  - Braukhane, Andy
A1  - Boden, Ralf Christian
A1  - Dumont, Etienne
A1  - Jahnke, Stephan Siegfried
A1  - Jetzschmann, Michael
A1  - Krüger, Hans
A1  - Lange, Michael
A1  - Gomez, Antonio Martelo
A1  - Massonett, Didier
A1  - Okada, Tatsuaki
A1  - Sagliano, Marco
A1  - Sasaki, Kaname
A1  - Schröder, Silvio
A1  - Sippel, Martin
A1  - Skoczylas, Thomas
A1  - Wejmo, Elisabet
T1  - Small landers and separable sub-spacecraft for near-term solar sails
T2  - The Fourth International Symposium on Solar Sailing 2017
N2  - 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.
KW  - Small Solar System Body Lander
KW  - Small Spacecraft
KW  - PHILAE
KW  - MASCOT
KW  - Solar Power Sail
Y1  - 2017
N1  - The Fourth International Symposium on Solar Sailing 2017, 17-20 January 2017. Kyoto Research Park, Kyoto, Japan
SP  - 1
EP  - 10
ER  - 
TY  - CHAP
A1  - Grundmann, Jan Thimo
A1  - Bauer, Waldemar
A1  - Boden, Ralf
A1  - Ceriotti, Matteo
A1  - Chand, Suditi
A1  - Cordero, Federico
A1  - Dachwald, Bernd
A1  - Dumont, Etienne
A1  - Grimm, Christian D.
A1  - Heiligers, Jeannette
A1  - Herčík, David
A1  - Hérique, Alain
A1  - Ho, Tra-Mi
A1  - Jahnke, Rico
A1  - Kofman, Wlodek
A1  - Lange, Caroline
A1  - Lichtenheldt, Roy
A1  - McInnes, Colin
A1  - Meß, Jan-Gerd
A1  - Mikschl, Tobias
A1  - Mikulz, Eugen
A1  - Montenegro, Sergio
A1  - Moore, Iain
A1  - Pelivan, Ivanka
A1  - Peloni, Alessandro
A1  - Plettemeier, Dirk
A1  - Quantius, Dominik
A1  - Reershemius, Siebo
A1  - Renger, Thomas
A1  - Riemann, Johannes
A1  - Rogez, Yves
A1  - Ruffer, Michael
A1  - Sasaki, Kaname
A1  - Schmitz, Nicole
A1  - Seboldt, Wolfgang
A1  - Seefeldt, Patric
A1  - Spietz, Peter
A1  - Spröwitz, Tom
A1  - Sznajder, Maciej
A1  - Tóth, Norbert
A1  - Vergaaij, Merel
A1  - Viavattene, Giulia
A1  - Wejmo, Elisabet
A1  - Wiedemann, Carsten
A1  - Wolff, Friederike
A1  - Ziach, Christian
T1  - 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
T2  - 70th International Astronautical Congress (IAC)
KW  - system engineering
KW  - small solar system body characterisation
KW  - small spacecraft solar sail
KW  - small spacecraft asteroid lander
KW  - responsive space
Y1  - 2019
SN  - 9781713814856
N1  - 70th International Astronautical Congress (IAC), Washington D.C., United States, 21-25 October 2019
SP  - 1
EP  - 7
ER  - 
TY  - CHAP
A1  - Grundmann, Jan Thimo
A1  - Bauer, Waldemar
A1  - Boden, Ralf Christian
A1  - Ceriotti, Matteo
A1  - Cordero, Federico
A1  - Dachwald, Bernd
A1  - Dumont, Etienne
A1  - Grimm, Christian D.
A1  - Hercik, D.
A1  - Herique, A.
A1  - Ho, Tra-Mi
A1  - Jahnke, Rico
A1  - Kofman, Wlodek
A1  - Lange, Caroline
A1  - Lichtenheldt, Roy
A1  - McInnes, Colin R.
A1  - Mikschl, Tobias
A1  - Mikulz, Eugen
A1  - Montenegro, Sergio
A1  - Moore, Iain
A1  - Pelivan, Ivanka
A1  - Peloni, Alessandro
A1  - Plettemeier, Dirk
A1  - Quantius, Dominik
A1  - Reershemius, Siebo
A1  - Renger, Thomas
A1  - Riemann, Johannes
A1  - Rogez, Yves
A1  - Ruffer, Michael
A1  - Sasaki, Kaname
A1  - Schmitz, Nicole
A1  - Seboldt, Wolfgang
A1  - Seefeldt, Patric
A1  - Spietz, Peter
A1  - Spröwitz, Tom
A1  - Sznajder, Maciej
A1  - Toth, Norbert
A1  - Viavattene, Giulia
A1  - Wejmo, Elisabet
A1  - Wolff, Friederike
A1  - Ziach, Christian
T1  - Responsive integrated small spacecraft solar sail and payload design concepts and missions
T2  - Conference: 5th International Symposium on Solar Sailing (ISSS 2019)
N2  - 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.
Y1  - 2019
N1  - Conference: 5th International Symposium on Solar Sailing (ISSS 2019)At: Aachen, Germany
ER  - 
TY  - CHAP
A1  - Grundmann, Jan Thimo
A1  - Meß, Jan-Gerd
A1  - Biele, Jens
A1  - Seefeldt, Patric
A1  - Dachwald, Bernd
A1  - Spietz, Peter
A1  - Grimm, Christian D.
A1  - Spröwitz, Tom
A1  - Lange, Caroline
A1  - Ulamec, Stephan
T1  - Small spacecraft in small solar system body applications
T2  - IEEE Aerospace Conference 2017, Big Sky, Montana, USA
Y1  - 2017
SN  - 978-1-5090-1613-6
U6  - https://doi.org/10.1109/AERO.2017.7943626
SP  - 1
EP  - 20
ER  - 
TY  - CHAP
A1  - Grundmann, Jan Thimo
A1  - Borella, Laura
A1  - Ceriotti, Matteo
A1  - Chand, Suditi
A1  - Cordero, Federico
A1  - Dachwald, Bernd
A1  - Fexer, Sebastian
A1  - Grimm, Christian D.
A1  - Hendrikse, Jeffrey
A1  - Herčík, David
A1  - Herique, Alain
A1  - Hillebrandt, Martin
A1  - Ho, Tra-Mi
A1  - Kesseler, Lars
A1  - Laabs, Martin
A1  - Lange, Caroline
A1  - Lange, Michael
A1  - Lichtenheldt, Roy
A1  - McInnes, Colin R.
A1  - Moore, Iain
A1  - Peloni, Alessandro
A1  - Plettenmeier, Dirk
A1  - Quantius, Dominik
A1  - Seefeldt, Patric
A1  - Venditti, Flaviane c. F.
A1  - Vergaaij, Merel
A1  - Viavattene, Giulia
A1  - Virkki, Anne K.
A1  - Zander, Martin
T1  - More bucks for the bang: new space solutions, impact tourism and one unique science & engineering opportunity at T-6 months and counting
T2  - 7th IAA Planetary Defense Conference
N2  - 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.
Y1  - 2021
N1  - 7th IAA Planetary Defense Conference, Vienna, Austria, 26-30 April 2021
ER  - 
TY  - CHAP
A1  - Grundmann, Jan Thimo
A1  - Bauer, Wlademar
A1  - Borchers, Kai
A1  - Dumont, Etienne
A1  - Grimm, Christian D.
A1  - Ho, Tra-Mi
A1  - Jahnke, Rico
A1  - Koch, Aaron D.
A1  - Lange, Caroline
A1  - Maiwald, Volker
A1  - Meß, Jan-Gerd
A1  - Mikulz, Eugen
A1  - Quantius, Dominik
A1  - Reershemius, Siebo
A1  - Renger, Thomas
A1  - Sasaki, Kaname
A1  - Seefeldt, Patric
A1  - Spietz, Peter
A1  - Spröwitz, Tom
A1  - Sznajder, Maciej
A1  - Toth, Norbert
A1  - Ceriotti, Matteo
A1  - McInnes, Colin
A1  - Peloni, Alessandro
A1  - Biele, Jens
A1  - Krause, Christian
A1  - Dachwald, Bernd
A1  - Hercik, David
A1  - Lichtenheldt, Roy
A1  - Wolff, Friederike
A1  - Koncz, Alexander
A1  - Pelivan, Ivanka
A1  - Schmitz, Nicole
A1  - Boden, Ralf
A1  - Riemann, Johannes
A1  - Seboldt, Wolfgang
A1  - Wejmo, Elisabet
A1  - Ziach, Christian
A1  - Mikschl, Tobias
A1  - Montenegro, Sergio
A1  - Ruffer, Michael
A1  - Cordero, Federico
A1  - Tardivel, Simon
T1  - Solar sails for planetary defense & high-energy missions
T2  - IEEE Aerospace Conference Proceedings
N2  - 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.
Y1  - 2019
U6  - https://doi.org/10.1109/AERO.2019.8741900
N1  - AERO 2019; Big Sky; United States; 2 March 2019 through 9 March 2019
SP  - 1
EP  - 21
ER  -