TY  - CHAP
A1  - Götten, Falk
A1  - Finger, Felix
A1  - Havermann, Marc
A1  - Braun, Carsten
A1  - Marino, Matthew
A1  - Bil, Cees
T1  - A highly automated method for simulating airfoil characteristics at low Reynolds number using a RANS - transition approach
T2  - Deutscher Luft- und Raumfahrtkongress - DLRK 2019. Darmstadt, Germany
Y1  - 2019
U6  - https://doi.org/10.25967/490026
SP  - 1
EP  - 14
ER  - 
TY  - CHAP
A1  - Funke, Harald
A1  - Beckmann, Nils
A1  - Abanteriba, Sylvester
T1  - Development and Testing of a FuelFlex Dry-Low-NOx Micromix Combustor for Industrial Gas Turbine Applications With Variable Hydrogen Methane Mixtures
T2  - ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition.  June 17–21, 2019 Phoenix, Arizona, USA. Volume 4A: Combustion, Fuels, and Emissions
Y1  - 2019
SN  - 978-0-7918-5861-5
U6  - https://doi.org/10.1115/GT2019-90095
ER  - 
TY  - CHAP
A1  - Götten, Falk
A1  - Finger, Felix
A1  - Braun, Carsten
A1  - Havermann, Marc
A1  - Bil, C.
A1  - Gomez, F.
T1  - Empirical Correlations for Geometry Build-Up of Fixed Wing Unmanned Air Vehicles
T2  - APISAT 2018: The Proceedings of the 2018 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2018)
N2  - The results of a statistical investigation of 42 fixed-wing, small to medium sized (20 kg−1000 kg) reconnaissance unmanned air vehicles (UAVs) are presented. Regression analyses are used to identify correlations of the most relevant geometry dimensions with the UAV’s maximum take-off mass. The findings allow an empirical based geometry-build up for a complete unmanned aircraft by referring to its take-off mass only. This provides a bridge between very early design stages (initial sizing) and the later determination of shapes and dimensions. The correlations might be integrated into a UAV sizing environment and allow designers to implement more sophisticated drag and weight estimation methods in this process. Additional information on correlation factors for a rough drag estimation methodology indicate how this technique can significantly enhance the accuracy of early design iterations.
KW  - Unmanned Air Vehicle
KW  - Geometry
KW  - Correlations
KW  - Statistics
KW  - Drag
Y1  - 2019
SN  - 978-981-13-3305-7
U6  - https://doi.org/10.1007/978-981-13-3305-7_109
N1  - APISAT 2018 - Asia-Pacific International Symposium on Aerospace Technology. 16-18 October 2018. Chengdu, China.


Lecture Notes in Electrical Engineering (LNEE, volume 459)
SP  - 1365
EP  - 1381
PB  - Springer
CY  - Singapore
ER  - 
TY  - CHAP
A1  - Finger, Felix
A1  - Götten, Falk
A1  - Braun, Carsten
A1  - Bil, Cees
T1  - Cost Estimation Methods for Hybrid-Electric General Aviation Aircraft
T2  - Asia Pacific International Symposium on Aerospace Technology. APISAT 2019
Y1  - 2019
SP  - 1
EP  - 13
ER  - 
TY  - CHAP
A1  - Finger, Felix
A1  - Braun, Carsten
A1  - Bil, Cees
T1  - Impact of Engine Failure Constraints on the Initial Sizing of Hybrid-Electric GA Aircraft
T2  - AIAA Scitech 2019 Forum
Y1  - 2019
U6  - https://doi.org/10.2514/6.2019-1812
N1  - AIAA Scitech Forum, 2019; San Diego; United States; 7 January 2019 through 11 January 2019
ER  - 
TY  - CHAP
A1  - Baader, Fabian
A1  - Keller, Denis
A1  - Lehmann, Raphael
A1  - Gerber, Lukas
A1  - Reiswich, Martin
A1  - Dachwald, Bernd
A1  - Förstner, Roger
T1  - Operating melting probes for ice penetration under sublimation  conditions and in reduced gravity on a sounding rocket
T2  - Proceedings of the 24th ESA Symposium on European Rocket and Balloon Programmes and related Research
Y1  - 2019
SN  - 0379-6566
N1  - 24th PAC Symposium 2019
ER  - 
TY  - CHAP
A1  - Quitter, Julius
A1  - Marino, Matthew
A1  - Bauschat, J.-Michael
T1  - Highly Non-Planar Aircraft Configurations: Estimation of Flight Mechanical Derivatives Using Low-Order Methods
T2  - Deutscher Luft- und Raumfahrtkongress 2019, DLRK 2019. Darmstadt, Germany
Y1  - 2019
ER  - 
TY  - CHAP
A1  - Götten, Falk
A1  - Finger, Felix
T1  - Conceptual Design of a Modular 150 kg Vertical Take-off and Landing Unmanned Aerial Vehicle
T2  - Deutscher Luft- und Raumfahrtkongress - DLRK 2019. Darmstadt, Germany
Y1  - 2019
SP  - 1
EP  - 10
ER  - 
TY  - CHAP
A1  - Horikawa, Atsushi
A1  - Okada, Kunio
A1  - Uto, Takahiro
A1  - Uchiyama, Yuta
A1  - Wirsum, Manfred
A1  - Funke, Harald
A1  - Kusterer, Karsten
T1  - Application of Low NOx Micro-mix Hydrogen Combustion to 2MW Class Industrial Gas Turbine Combustor
T2  - Proceedings of International Gas Turbine Congress 2019 Tokyo, November 17-22, 2019, Tokyo, Japan
Y1  - 2019
SN  - 978-4-89111-010-9
N1  - IGTC-2019-129
SP  - 1
EP  - 6
ER  - 
TY  - CHAP
A1  - Striegan, Constantin J. D.
A1  - Struth, Benjamin
A1  - Dickhoff, Jens
A1  - Kusterer, Karsten
A1  - Funke, Harald
A1  - Bohn, Dieter
T1  - Numerical Simulations of the Micromix DLN Hydrogen Combustion Technology with LES and Comparison to Results of RANS and Experimental Data
T2  - Proceedings of International Gas Turbine Congress 2019 Tokyo, November 17-22, 2019, Tokyo, Japan.
Y1  - 2019
SN  - 978-4-89111-010-9
N1  - IGCT-2019-147
SP  - 1
EP  - 9
ER  - 
TY  - CHAP
A1  - Hailer, Benjamin
A1  - Weber, Tobias
A1  - Arent, Jan-Christoph
T1  - Manufacturing Process Simulation for Autoclave-Produced Sandwich Structures
T2  - Proceedings of SAMPE Europe Conference 2019, Nantes, France
Y1  - 2019
SP  - 1
EP  - 8
ER  - 
TY  - CHAP
A1  - Weber, Tobias
A1  - Englhard, Markus
A1  - Hailer, Benjamin
A1  - Arent, Jan-Christoph
T1  - Manufacturing Process Simulation for the Prediction of Tool-Part-Interaction and Ply Wrinkling
T2  - Proceedings of SAMPE Europe Conference 2019, Nantes, France
Y1  - 2019
SP  - 1
EP  - 10
ER  - 
TY  - CHAP
A1  - Bergmann, Kevin
A1  - Gräbener, Josefine
A1  - Wild, Dominik
A1  - Ulfers, H.
A1  - Czupalla, Markus
T1  - Study on thermal stabilization of a GEO-stationary telescope baffling system by integral application of phase change material
T2  - International Conference on Environmental Systems
N2  - The utilization of phase change material (PCM) for latent heat storage and thermal control of spacecraft has been demonstrated in the past in few missions only. One limiting factor was the fact that all concepts developed so far envisioned the PCM to be applied as an additional capacitor, encapsulated in its own housing, leading to mass, efficiency and accommodation challenges. Recently, the application of PCM within the scan cavity of a GEOS type satellite has been suggested, in order to tackle thermal issues due to direct sun intrusion (Choi, M., 2014). However, the application of PCM in such complex mechanical structures is extremely challenging. A new concept to tackle this issue is currently under development at the FH Aachen University of Applied Sciences. The concept "Infused Thermal Solutions (ITS)" is based on the idea to 3D print metallic structures in their regular functional shape, but double walled with internal lattice support structures, allowing the infusion of a PCM layer directly into the voids and eliminating the need for additional parts and interfaces. Together with OHB System, FH Aachen theoretically studied the application of this technology to the Meteosat Third Generation (MTG) Infra-Red Sounder (IRS) instrument. The study focuses on the scan cavity and entrance baffling assembly (EBA) of the IRS. It consists of thermal analyses, 3D-redesign and bread boarding of a scaled and PCM infused EBA version. In the thermal design of the alternative EBA, PCM was applied directly into the EBA, simulating the worst hot case sun intrusion of the mission. By applying 4kg of PCM (to a 60kg baffle) the EBA temperature excursions during sun intrusion were limited from 140K to 30K, leading to a significant thermo-opto-elastic performance gain. This paper introduces the ITS concept development status.
Y1  - 2019
N1  - 49th International Conference on Environmental Systems, 7-11 July 2019, Boston, Massachusetts ; ICES-2019-72
SP  - 1
EP  - 14
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  - Montenegro, Sergio
A1  - Moore, Iain
A1  - Pelivan, Ivanka
A1  - Peloni, Alessandro
A1  - Plettenmeier, 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 exploration and asteroid characterization through integrated solar sail and lander development using small spacecraft technologies
T2  - IAA Planetary Defense Conference
N2  - 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.
Y1  - 2019
N1  - Conference: IAA Planetary Defense ConferenceAt: Washington DC, USA
29.04-03.05.2019
ER  - 
TY  - CHAP
A1  - Finger, Felix
A1  - Khalsa, R.
A1  - Kreyer, Jörg
A1  - Mayntz, Joscha
A1  - Braun, Carsten
A1  - Dahmann, Peter
A1  - Esch, Thomas
A1  - Kemper, Hans
A1  - Schmitz, O.
A1  - Bragard, Michael
T1  - An approach to propulsion system modelling for the conceptual design of hybrid-electric general aviation aircraft
T2  - Deutscher Luft- und Raumfahrtkongress 2019, 30.9.-2.10.2019, Darmstadt
N2  - In this paper, an approach to propulsion system modelling for hybrid-electric general aviation aircraft is presented. Because the focus is on general aviation aircraft, only combinations of electric motors and reciprocating combustion engines are explored. Gas turbine hybrids will not be considered. The level of the component's models is appropriate for the conceptual design stage. They are simple and adaptable, so that a wide range of designs with morphologically different propulsive system architectures can be quickly compared. Modelling strategies for both mass and efficiency of each part of the propulsion system (engine, motor, battery and propeller) will be presented.
Y1  - 2019
ER  - 
TY  - CHAP
A1  - Ludowicy, Jonas
A1  - Rings, René
A1  - Finger, Felix
A1  - Braun, Carsten
A1  - Bil, Cees
T1  - Impact of Propulsion Technology Levels on the Sizing and Energy Consumption for Serial HybridElectric General Aviation Aircraft
T2  - Asia Pacific International Symposium on Aerospace Technology. APISAT 2019
Y1  - 2019
ER  - 
TY  - CHAP
A1  - Finger, Felix
A1  - Götten, Falk
A1  - Braun, Carsten
A1  - Bil, C.
T1  - On Aircraft Design Under the Consideration of Hybrid-Electric Propulsion Systems
T2  - APISAT 2018: The Proceedings of the 2018 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2018)
N2  - A hybrid-electric propulsion system combines the advantages of fuel-based systems and battery powered systems and offers new design freedom. To take full advantage of this technology, aircraft designers must be aware of its key differences, compared to conventional, carbon-fuel based, propulsion systems. This paper gives an overview of the challenges and potential benefits associated with the design of aircraft that use hybrid-electric propulsion systems. It offers an introduction of the most popular hybrid-electric propulsion architectures and critically assess them against the conventional and fully electric propulsion configurations. The effects on operational aspects and design aspects are covered. Special consideration is given to the application of hybrid-electric propulsion technology to both unmanned and vertical take-off and landing aircraft. The authors conclude that electric propulsion technology has the potential to revolutionize aircraft design. However, new and innovative methods must be researched, to realize the full benefit of the technology.
KW  - Hybrid-electric aircraft
KW  - Aircraft design
KW  - Design rules
KW  - Green aircraft
Y1  - 2019
SN  - 978-981-13-3305-7
U6  - https://doi.org/10.1007/978-981-13-3305-7_99
N1  - APISAT 2018 - Asia-Pacific International Symposium on Aerospace Technology. 16-18 October 2018. Chengdu, China.

Lecture Notes in Electrical Engineering (LNEE, volume 459)
SP  - 1261
EP  - 1272
PB  - Springer
CY  - Singapore
ER  - 
TY  - CHAP
A1  - Jean-Pierre P., de Vera
A1  - Baque, Mickael
A1  - Billi, Daniela
A1  - Böttger, Ute
A1  - Bulat, Sergey
A1  - Czupalla, Markus
A1  - Dachwald, Bernd
A1  - de la Torre, Rosa
A1  - Elsaesser, Andreas
A1  - Foucher, Frédéric
A1  - Korsitzky, Hartmut
A1  - Kozyrovska, Natalia
A1  - Läufer, Andreas
A1  - Moeller, Ralf
A1  - Olsson-Francis, Karen
A1  - Onofri, Silvano
A1  - Sommer, Stefan
A1  - Wagner, Dirk
A1  - Westall, Frances
T1  - The search for life on Mars and in the Solar System - strategies, logistics and infrastructures
T2  - 69th International Astronautical Congress (IAC)
N2  - 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.
KW  - life detection
KW  - Mars
KW  - icy moons
KW  - habitability
KW  - space missions
Y1  - 2018
N1  - 69th International Astronautical Congress (IAC), Bremen, Germany, 1-5 October 2018.
SP  - 1
EP  - 8
ER  - 
TY  - CHAP
A1  - Schulze, Sven
A1  - Mühleisen, M.
A1  - Feyerl, Günter
T1  - Adaptive energy management strategy for a heavy-duty truck with a P2-hybrid topology
T2  - 18. Internationales Stuttgarter Symposium. Proceedings
Y1  - 2018
U6  - https://doi.org/10.1007/978-3-658-21194-3
SP  - 75
EP  - 89
PB  - Springer Vieweg
CY  - Wiesbaden
ER  - 
TY  - CHAP
A1  - Grundmann, Jan Thimo
A1  - Bauer, Waldemar
A1  - Borchers, Kai
A1  - Dumont, Etienne
A1  - Grimm, Christian D.
A1  - Ho, Tra-Mi
A1  - Jahnke, Rico
A1  - Lange, Caroline
A1  - Maiwald, Volker
A1  - Mikulz, Eugen
A1  - Quantius, Dominik
A1  - Reershemius, Siebo
A1  - Renger, Thomas
A1  - Riemann, Johannes
A1  - Sasaki, Kaname
A1  - Seefeldt, Patric
A1  - Spietz, Peter
A1  - Spröwitz, Tom
A1  - Toth, Norbert
A1  - Wejmo, Elisabet
A1  - Biele, Jens
A1  - Krause, Christian
A1  - Cerotti, Matteo
A1  - Peloni, Alessandro
A1  - Dachwald, Bernd
T1  - Small Spacecraft Solar Sailing for Small Solar System Body Multiple Rendezvous and Landing
T2  - 2018 IEEE Aerospace Conference : 3-10 March 2018
Y1  - 2018
SN  - 978-1-5386-2014-4
ER  - 
TY  - CHAP
A1  - Grundmann, Jan Thimo
A1  - Bauer, Waldemar
A1  - Biele, Jens
A1  - Boden, Ralf
A1  - Ceriotti, Matteo
A1  - Cordero, Federico
A1  - Dachwald, Bernd
A1  - Dumont, Etienne
A1  - Grimm, Christian
A1  - Herčík, David
A1  - Herique, Alain
A1  - Ho, Tra-Mi
A1  - Jahnke, Rico
A1  - Koch, Aaron
A1  - Kofman, Wlodek
A1  - Koncz, Alexander
A1  - Krause, Christian
A1  - Lange, Caroline
A1  - Lichtenheldt, Roy
A1  - Maiwald, Volker
A1  - Mikschl, Tobias
A1  - Mikulz, Eugen
A1  - Montenegro, Sergio
A1  - Pelivan, Ivanka
A1  - Peloni, Alessandro
A1  - Plettemeier, Dirk
A1  - Quantius, Dominik
A1  - Reershemius, Siebo
A1  - Renger, Thomas
A1  - Riemann, Johannes
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  - Tardivel, Simon
A1  - Toth, Norbert
A1  - Wejmo, Elisabet
A1  - Wolff, Friederike
A1  - Ziach, Christian
T1  - Efficient massively parallel prospection for ISRU by multiple near-earth asteroid rendezvous using near-term solar sails and'now-term'small spacecraft solutions
T2  - 2nd Asteroid Science Intersections with In-Space Mine Engineering – ASIME 2018
N2  - 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.
Y1  - 2018
N1  - 2nd Asteroid Science Intersections with In-Space Mine Engineering – ASIME 2018
16-17 April 2018, Belval, Luxembourg
SP  - 1
EP  - 33
ER  - 
TY  - CHAP
A1  - Grundmann, Jan Thimo
A1  - Bauer, Waldemar
A1  - Biele, Jens
A1  - Boden, Ralf
A1  - Ceriotti, Matteo
A1  - Cordero, Federico
A1  - Dachwald, Bernd
A1  - Dumont, Etienne
A1  - Grimm, Christian D.
A1  - Herčík, David
A1  - Ho, Tra-Mi
A1  - Jahnke, Rico
A1  - Koch, Aaron D
A1  - Koncz, Alexander
A1  - Krause, Christian
A1  - Lange, Caroline
A1  - Lichtenheldt, Roy
A1  - Maiwald, Volker
A1  - Mikschl, Tobias
A1  - Mikulz, Eugen
A1  - Montenegro, Sergio
A1  - Pelivan, Ivanka
A1  - Peloni, Alessandro
A1  - Quantius, Dominik
A1  - Reershemius, Siebo
A1  - Renger, Thomas
A1  - Riemann, Johannes
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  - Tardivel, Simon
A1  - Tóth, Norbert
A1  - Wejmo, Elisabet
A1  - Wolff, Friederike
A1  - Ziach, Christian
T1  - Small spacecraft based multiple near-earth asteroid rendezvous and landing with near-term solar sails and ‘Now-Term ‘technologies
T2  - 69 th International Astronautical Congress (IAC)
N2  - 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.
KW  - multiple NEA rendezvous
KW  - solar sail
KW  - GOSSAMER-1
KW  - MASCOT
KW  - small spacecraft
Y1  - 2018
N1  - 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/
SP  - 1
EP  - 18
ER  - 
TY  - CHAP
A1  - Götten, Falk
A1  - Havermann, Marc
A1  - Braun, Carsten
A1  - Gomez, Francisco
A1  - Bil, Cees
T1  - On the Applicability of Empirical Drag Estimation Methods for Unmanned Air Vehicle Design   Read More: https://arc.aiaa.org/doi/10.2514/6.2018-3192
T2  - 2018 Aviation Technology, Integration, and Operations Conference, AIAA AVIATION Forum
Y1  - 2018
U6  - https://doi.org/10.2514/6.2018-3192
SN  - 1533-385X
N1  - AIAA 2018-3192
SP  - Article 3192
ER  - 
TY  - CHAP
A1  - Waldmann, Christoph
A1  - Vera, Jean-Pierre de
A1  - Dachwald, Bernd
A1  - Strasdeit, Henry
A1  - Sohl, Frank
A1  - Hanff, Hendrik
A1  - Kowalski, Julia
A1  - Heinen, Dirk
A1  - Macht, Sabine
A1  - Bestmann, Ulf
A1  - Meckel, Sebastian
A1  - Hildebrandt, Marc
A1  - Funke, Oliver
A1  - Gehrt, Jan-Jöran
T1  - Search for life in ice-covered oceans and lakes beyond Earth
T2  - 2018 IEEE/OES Autonomous Underwater Vehicle Workshop, Proceedings November 2018, Article number 8729761
N2  - 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.
KW  - Planetary exploration
KW  - Jupiter
KW  - ice moons
KW  - underwater vehicle
KW  - Antarctica
Y1  - 2018
U6  - https://doi.org/10.1109/AUV.2018.8729761
ER  - 
TY  - CHAP
A1  - Finger, Felix
A1  - Götten, Falk
A1  - Braun, Carsten
T1  - Initial Sizing for a Family of Hybrid-Electric VTOL General Aviation Aircraft
T2  - 67. Deutscher Luft- und Raumfahrtkongress 2018
Y1  - 2018
ER  - 
TY  - CHAP
A1  - Ludowicy, Jonas
A1  - Rings, René
A1  - Finger, Felix
A1  - Braun, Carsten
T1  - Sizing Studies of Light Aircraft with Serial Hybrid Propulsion Systems
T2  - Luft- und Raumfahrt - Digitalisierung und Vernetzung : Deutscher Luft- und Raumfahrtkongress 2018. 4. - 6. September 2018 - Friedrichshafen
Y1  - 2018
ER  - 
TY  - CHAP
A1  - Ludowicy, Jonas
A1  - Rings, René
A1  - Finger, Felix
A1  - Braun, Carsten
T1  - Sizing Studies of Light Aircraft with Parallel Hybrid Propulsion Systems
T2  - Deutscher Luft- und Raumfahrtkongress 2018
Y1  - 2018
U6  - https://doi.org/10.25967/480227
ER  - 
TY  - CHAP
A1  - Finger, Felix
A1  - Braun, Carsten
A1  - Bil, Cees
T1  - Case studies in initial sizing for hybrid-electric general aviation aircraft
T2  - 2018 AIAA/IEEE Electric Aircraft Technologies Symposium, Cincinnati, Ohio
Y1  - 2018
U6  - https://doi.org/10.2514/6.2018-5005
ER  - 
TY  - CHAP
A1  - Blome, Hans-Joachim
T1  - Über die kulturelle Bedeutung der Raumfahrt
T2  - Überleben im Weltraum. Auf dem Weg zu neuen Grenzen. 21. Berliner Kolloquium der Daimler und Benz Stiftung 24. Mai 2017
Y1  - 2018
SP  - 5
EP  - 5
ER  - 
TY  - CHAP
A1  - Funke, Harald
A1  - Beckmann, Nils
A1  - Abanteriba, Sylvester
T1  - A comparison of complex chemistry mechanisms for hydrogen methane blends based on the Sandia / Sydney Bluff-Body Flame HM1
T2  - Proceedings of the Eleventh Asia‐Pacific Conference on Combustion (ASPACC 2017), New South Wales, Australia, 10-14 December 2017
Y1  - 2017
SN  - 978-1-5108-5646-2
SP  - 262
EP  - 265
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  - 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  - Peloni, Alessandro
A1  - Dachwald, Bernd
A1  - Ceriotti, Matteo
T1  - Multiple NEA rendezvous mission: Solar sailing options
T2  - Fourth International Symposium on Solar Sailing
N2  - 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.
KW  - Multiphase
KW  - Trajectory Optimization
KW  - Automated Optimization
KW  - Gossamer
KW  - Sequence-Search
Y1  - 2017
N1  - Fourth International Symposium on Solar Sailing (ISSS 2017), Kyoto, Japan, 17-20 Jan 2017.
http://www.jsforum.or.jp/ISSS2017/
SP  - 1
EP  - 11
ER  - 
TY  - CHAP
A1  - Peterson, Leif Arne
A1  - Röth, Thilo
A1  - Uibel, Thomas
ED  - Uibel, Thormas
ED  - Peterson, Leif Arne
ED  - Baumann, Marcus
T1  - Holzwerkstoffe in Karosseriestrukturen
T2  - Tagungsband Aachener Holzbautagung 2017
Y1  - 2017
SN  - 2197-4489
SP  - 34
EP  - 45
ER  - 
TY  - CHAP
A1  - Barnat, Miriam
A1  - Knutzen, S.
ED  - Mai, Andreas
T1  - Erfolgsstrategien für organisationales Lernen
T2  - Hochschulwege 2015 : Wie verändern Projekte die Hochschulen? ; Dokumentation der Tagung in Weimar im März 2015
Y1  - 2017
SN  - 978-3-7439-1763-7
SP  - 91
EP  - 108
PB  - tredition
CY  - Hamburg
ER  - 
TY  - CHAP
A1  - Funke, Harald
A1  - Keinz, Jan
A1  - Hendrick, P.
T1  - Experimental Evaluation of the Pollutant and Noise Emissions of the GTCP 36-300 Gas Turbine Operated with Kerosene and a Low NOX Micromix Hydrogen Combustor
T2  - 7th European Conference for Aeronautics and Space Sciences, EUCASS 2017
Y1  - 2017
U6  - https://doi.org/10.13009/EUCASS2017-125
ER  - 
TY  - CHAP
A1  - Striegan, C.
A1  - Haj Ayed, A.
A1  - Funke, Harald
A1  - Loechle, S.
A1  - Kazari, M.
A1  - Horikawa, A.
A1  - Okada, K.
A1  - Koga, K.
T1  - Numerical combustion and heat transfer simulations and validation for a hydrogen fueled "micromix" test combustor in industrial gas turbine applications
T2  - Proceedings of the ASME Turbo Expo
Y1  - 2017
SN  - 978-079185085-5
U6  - https://doi.org/10.1115/GT2017-64719
N1  - ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition, GT 2017; Charlotte; United States; 26 June 2017 through 30 June 2017
IS  - Volume Part F130041-4B, 2017
ER  - 
TY  - CHAP
A1  - Ayed, Anis Haj
A1  - Striegan, Constantin J. D.
A1  - Kusterer, Karsten
A1  - Funke, Harald
A1  - Kazari, M.
A1  - Horikawa, Atsushi
A1  - Okada, Kunio
T1  - Automated design space exploration of the hydrogen fueled "Micromix" combustor technology
N2  - Combined with the use of renewable energy sources for
its production, Hydrogen represents a possible alternative gas
turbine fuel for future low emission power generation. Due to
its different physical properties compared to other fuels such
as natural gas, well established gas turbine combustion
systems cannot be directly applied for Dry Low NOx (DLN)
Hydrogen combustion. This makes the development of new
combustion technologies an essential and challenging task
for the future of hydrogen fueled gas turbines.
The newly developed and successfully tested “DLN
Micromix” combustion technology offers a great potential to
burn hydrogen in gas turbines at very low NOx emissions.
Aiming to further develop an existing burner design in terms
of increased energy density, a redesign is required in order to
stabilise the flames at higher mass flows and to maintain low
emission levels.
For this purpose, a systematic design exploration has
been carried out with the support of CFD and optimisation
tools to identify the interactions of geometrical and design
parameters on the combustor performance. Aerodynamic
effects as well as flame and emission formation are observed
and understood time- and cost-efficiently. Correlations
between single geometric values, the pressure drop of the
burner and NOx production have been identified as a result.
This numeric methodology helps to reduce the effort of
manufacturing and testing to few designs for single
validation campaigns, in order to confirm the flame stability
and NOx emissions in a wider operating condition field.
Y1  - 2017
N1  - Proceedings of the 1st Global Power and Propulsion Forum
GPPF 2017, Jan 16-18, 2017, Zurich, Switzerland
SP  - 1
EP  - 8
ER  - 
TY  - CHAP
A1  - Funke, Harald
A1  - Beckmann, Nils
A1  - Keinz, Jan
A1  - Abanteriba, Sylvester
T1  - Numerical and Experimental Evaluation of a Dual-Fuel Dry-Low-NOx Micromix Combustor for Industrial Gas Turbine Applications
T2  - Proceedings of the ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. Volume 4B: Combustion, Fuels and Emissions. Charlotte, North Carolina, USA. June 26–30, 2017
N2  - The Dry-Low-NOx (DLN) Micromix combustion technology has been developed originally as a low emission alternative for industrial gas turbine combustors fueled with hydrogen. Currently the ongoing research process targets flexible fuel operation with hydrogen and syngas fuel.

The non-premixed combustion process features jet-in-crossflow-mixing of fuel and oxidizer and combustion through multiple miniaturized flames. The miniaturization of the flames leads to a significant reduction of NOx emissions due to the very short residence time of reactants in the flame.

The paper presents the results of a numerical and experimental combustor test campaign. It is conducted as part of an integration study for a dual-fuel (H2 and H2/CO 90/10 Vol.%) Micromix combustion chamber prototype for application under full scale, pressurized gas turbine conditions in the auxiliary power unit Honeywell Garrett GTCP 36-300.

In the presented experimental studies, the integration-optimized dual-fuel Micromix combustor geometry is tested at atmospheric pressure over a range of gas turbine operating conditions with hydrogen and syngas fuel. The experimental investigations are supported by numerical combustion and flow simulations. For validation, the results of experimental exhaust gas analyses are applied.

Despite the significantly differing fuel characteristics between pure hydrogen and hydrogen-rich syngas the evaluated dual-fuel Micromix prototype shows a significant low NOx performance and high combustion efficiency. The combustor features an increased energy density that benefits manufacturing complexity and costs.
Y1  - 2017
SN  - 978-0-7918-5085-5
U6  - https://doi.org/10.1115/GT2017-64795
N1  - Paper No. GT2017-64795, V04BT04A045
PB  - ASME
CY  - New York
ER  - 
TY  - CHAP
A1  - Grundmann, Jan Thimo
A1  - Boden, Ralf
A1  - Ceriotti, Matteo
A1  - Dachwald, Bernd
A1  - Dumont, Etienne
A1  - Grimm, Christian D.
A1  - Lange, Caroline
A1  - Lichtenheldt, Roy
A1  - Pelivan, Ivanka
A1  - Peloni, Alessandro
A1  - Riemann, Johannes
A1  - Spröwitz, Tom
A1  - Tardivel, Simon
T1  - Soil to sail-asteroid landers on near-term sailcraft as an evolution of the GOSSAMER small spacecraft solar sail concept for in-situ characterization
T2  - 5th IAA Planetary Defense Conference
KW  - multiple NEA rendezvous
KW  - solar sail
KW  - GOSSAMER-1
KW  - MASCOT
KW  - asteroid sample return
Y1  - 2017
N1  - 5th IAA Planetary Defense Conference – PDC 2017
15-19 May 2017, Tokyo, Japan
ER  - 
TY  - CHAP
A1  - Dachwald, Bernd
T1  - Radiation pressure force model for an ideal laser-enhanced solar sail
T2  - 4th International Symposium on Solar Sailing
N2  - 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.
Y1  - 2017
N1  - 4th International Symposium on Solar Sailing
17-20 January 2017, Kyōto, Japan
SP  - 1
EP  - 5
ER  - 
TY  - CHAP
A1  - Schildt, P.
A1  - Braun, Carsten
A1  - Marcocca, P.
T1  - Flight testing the extra 330LE flying testbed
T2  - 48th Annual International Symposium of the Society of Flight Test Engineers 2017
Y1  - 2017
SN  - 978-151085387-4
N1  - 48th Annual International Symposium of the Society of Flight Test Engineers 2017, SFTE 2017; Destin; United States; 30 October 2017 through 2 November 2017
SP  - 349
EP  - 362
ER  - 
TY  - CHAP
A1  - Czupalla, Markus
T1  - Pflanzen oder Maschinen - was läßt uns auf dem Mars überleben?
T2  - Überleben im Weltraum. Auf dem Weg zu neuen Grenzen. 21. Berliner Kolloquium der Daimler und Benz Stiftung 24. Mai 2017
Y1  - 2017
SP  - 12
EP  - 12
ER  - 
TY  - CHAP
A1  - Carzana, Livio
A1  - Dachwald, Bernd
A1  - Noomen, Ron
T1  - Model and trajectory optimization for an ideal laser-enhanced solar sail
T2  - 68th International Astronautical Congress
N2  - 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
Y1  - 2017
N1  - 68th International Astronautical Congress: Unlocking Imagination, Fostering Innovation and Strengthening Security, IAC 2017, 2017-09-25 → 2017-09-29, Adelaide, Australia
ER  - 
TY  - CHAP
A1  - Finger, Felix
A1  - Braun, Carsten
A1  - Bil, Cees
T1  - The Impact of Electric Propulsion on the Performance of VTOL UAVs
T2  - Deutscher Luft- und Raumfahrtkongress 2017, DLRK , München
Y1  - 2017
ER  - 
TY  - CHAP
A1  - Finger, Felix
A1  - Braun, Carsten
A1  - Bil, Cees
T1  - A Review of Configuration Design for Distributed Propulsion Transitioning VTOL Aircraft
T2  - Asia-Pacific International Symposium on Aerospace Technology 2017, APISAT 2017, Seoul, Korea
Y1  - 2017
ER  - 
TY  - CHAP
A1  - Kreyer, Jörg
A1  - Esch, Thomas
T1  - Simulation Tool for Predictive Control Strategies for an ORCSystem in Heavy Duty Vehicles
T2  - European GT Conference 2017
N2  - Scientific questions
- How can a non-stationary heat offering in the commercial vehicle be used to reduce fuel consumption?
- Which potentials offer route and environmental information among with predicted speed and load trajectories to increase the efficiency of a ORC-System?
Methods
- Desktop bound holistic simulation model for a heavy duty truck incl. an ORC System
- Prediction of massflows, temperatures and mixture quality (AFR) of exhaust gas
Y1  - 2017
N1  - European GT Conference 2017, 9.-10. Oktober 2017, Frankfurt a.M.
ER  - 
TY  - CHAP
A1  - Barnat, Miriam
A1  - Mergner, Julia
T1  - Forschungsbasierte Qualitätsentwicklung am Beispiel der Analyse von Lernprozessen und der Wirksamkeit von Förderprogrammen
T2  - 3. Internationale Tagung für Qualitätsmanagement und Qualitätsentwicklung im Hochschulbereich 2.-3. Februar 2017
Y1  - 2017
ER  - 
TY  - CHAP
A1  - Blome, Hans-Joachim
A1  - Gerzer, Rupert
A1  - Baumstark-Khan, Christa
A1  - Ewald, Reinhold
A1  - Heinicke, Christiane
A1  - Czupalla, Markus
A1  - Carter, Layne
A1  - Anderson, Molly
T1  - Überleben im Weltraum. Auf dem Weg zu neuen Grenzen. 21. Berliner Kolloquium der Daimler und Benz Stiftung 24. Mai 2017
Y1  - 2017
ER  - 
TY  - CHAP
A1  - Barnat, Miriam
A1  - Bosse, Elke
A1  - Mergner, Julia
A1  - Jänsch, Vanessa
T1  - Entwicklung studienrelevanter Kompetenzen im Zusammenspiel mit Studieneinstiegsangeboten
T2  - KoBF-Auswertungsworkshop 31.05.-01.06.2017
Y1  - 2017
ER  - 
TY  - CHAP
A1  - Hallmann, Marcus
A1  - Heidecker, Ansgar
A1  - Schlotterer, Markus
A1  - Dachwald, Bernd
T1  - GTOC8: results and methods of team 15 DLR
T2  - 26th AAS/AIAA Space Flight Mechanics Meeting, Napa, CA
N2  - 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.
Y1  - 2016
N1  - 26th AAS/AIAA Space Flight Mechanics Meeting, February 14-18, 2016, Napa, California, U.S.A. Napa, CA
ER  - 
TY  - CHAP
A1  - Rupp, Matthias
A1  - Kuperjans, Isabel
A1  - Schulze, Sven
ED  - Berns, Karsten
T1  - Energetische und ökologische Bewertung hybrider Antriebe im städtischen Busverkehr
T2  - Commercial vehicle technology 2016 : proceedings of the 4th Commercial Vehicle Technology Symposium (CVT 2016), March 8-10, 2016, University of Kaiserslautern, Kaiserslautern, Germany
N2  - In Anbetracht weltweit zunehmend strengerer klimapolitischer
Ziele steigt auch der Druck für Nutzfahrzeughersteller, effizientere und umweltfreundlichere
Technologien zu entwickeln. Den Blick bei der Bewertung dieser
ausschließlich auf die Fahrzeugnutzung zu richten, ist längst nicht mehr zufriedenstellend.
Im Rahmen dieser Analyse wird ein gegenwärtig auf dem Markt erwerblicher
und in deutschen Städten bereits seit Jahren betriebener Hybridbus
energetisch und ökologisch mit einem konventionell angetriebenen, nahezu baugleichen
Modell entlang des Lebensweges bewertet.
Nach Definition von Ziel und Untersuchungsrahmen wird ein Überblick auf bereits
durchgeführte Lebenszyklusanalysen zu Hybridbussen im Stadtverkehr gegeben
und Schlussfolgerungen für die anschließende Analyse abgeleitet. Diese
wird im Rahmen einer energetischen und ökologischen Bewertung beider Produktsysteme
anhand der Parameter "Primärenergieeinsatz" und "CO2äq Emissionen"
praktiziert. Der Fahrzeugrumpf beider Fahrzeuge des gleichen Modells
wird dabei als einheitlich angenommen, sodass bei dem Vergleich der Herstellung
vereinfacht nur die sich unterscheidenden Komponenten des Antriebstranges
berücksichtigt werden. Die Resultate der Wirkungsabschätzung werden als
Differenz des Hybridbusses gegenüber dem Referenzfahrzeug über die einzelnen
Lebenszyklusphasen dargestellt. Schließlich werden Prognosen getroffen, ab
welcher Strecke die bei der Herstellung erzeugten höheren CO2äq Emissionen
des Hybridantriebstranges gegenüber dem Referenzmodell ausgeglichen werden.
Y1  - 2016
SP  - 227
EP  - 237
PB  - Shaker
CY  - Aachen
ER  - 
TY  - CHAP
A1  - Funke, Harald
A1  - Keinz, Jan
A1  - Börner, S.
A1  - Hendrick, P.
A1  - Elsing, R.
T1  - Testing and analysis of the impact on engine cycle parameters and control system modifications using hydrogen or methane as fuel in an industrial gas turbine
T2  - Progress in propulsion physics ; Volume 8
Y1  - 2016
SN  - 978-5-94588-191-4
U6  - https://doi.org/10.1051/eucass/201608409
SP  - 409
EP  - 426
PB  - EDP Sciences
CY  - o.O.
ER  - 
TY  - CHAP
A1  - Wu, Ziyi
A1  - Kemper, Hans
T1  - The optimal 48 V – battery pack for a specific load profile of a heavy duty vehicle
T2  - 8. Internationale Fachtagung Kraftwerk Batterie : 26. – 27. April 2016, Münster, Deutschland
Y1  - 2016
ER  - 
TY  - CHAP
A1  - Neu, Eugen
A1  - Janser, Frank
A1  - Khatibi, Akbar A.
A1  - Orifici, Adrian C.
T1  - In-flight vibration-based structural health monitoring of aircraft wings
T2  - 30th Congress of the internatonal council of the aeronautical sciences : 25.-30. September 2016, Daejeon, Korea
N2  - This work presents a methodology for automated
damage-sensitive feature extraction and anomaly
detection under multivariate operational variability
for in-flight assessment of wings. The
method uses a passive excitation approach, i. e.
without the need for artificial actuation. The
modal system properties (natural frequencies and
damping ratios) are used as damage-sensitive
features. Special emphasis is placed on the use
of Fiber Bragg Grating (FBG) sensing technology
and the consideration of Operational and
Environmental Variability (OEV). Measurements
from a wind tunnel investigation with a composite
cantilever equipped with FBG and piezoelectric
sensors are used to successfully detect an impact
damage. In addition, the feasibility of damage
localisation and severity estimation is evaluated
based on the coupling found between damageand
OEV-induced feature changes.
Y1  - 2016
ER  - 
TY  - CHAP
A1  - Barnat, Miriam
A1  - Bosse, Elke
T1  - The challenge of creating meta-inferences: Combining data representing institutional and individual perspectives on first-year support in higher education
T2  - 9th Conference on Social Science Methodology of the International Sociological Association, Leicester, UK
Y1  - 2016
N1  - RC33 Conference 2016
SP  - 1
EP  - 20
ER  - 
TY  - CHAP
A1  - Kleine, Harald
A1  - Kallweit, Stephan
A1  - Michaux, Frank
A1  - Havermann, Marc
A1  - Olivier, Herbert
T1  - PIV Measurement of Shock Wave Diffraction
T2  - 18th International Symposium on Applications of Laser Techniques to Fluid Mechanics, 2016, Lissabon
Y1  - 2016
SP  - 1
EP  - 14
ER  - 
TY  - CHAP
A1  - Schleupen, Josef
A1  - Engemann, Heiko
A1  - Bagheri, Mohsen
A1  - Kallweit, Stephan
T1  - The potential of SMART climbing robot combined with a weatherproof cabin for rotor blade maintenance
T2  - 17th European Conference on Composite Materials – ECCM, Munich, Germany
Y1  - 2016
N1  - ECCM 17
SP  - 1
EP  - 8
ER  - 
TY  - CHAP
A1  - Hoeveler, Bastian
A1  - Janser, Frank
T1  - The aerodynamically optimized design of a fan-in-wing duct
T2  - Applied Aerodynamics Research Conference 2016, Bristol, GB, Jul 19-21, 2016
Y1  - 2016
SN  - 1-85768-371-4
N1  - G1-3-paper.pdf
SP  - 1
EP  - 10
ER  - 
TY  - CHAP
A1  - Otten, D.
A1  - Schmidt, M.
A1  - Weber, Tobias
T1  - Advances in Determination of Material Parameters for Functional Simulations Based on Process Simulations
T2  - SAMPE Europe Conference 16 Liege
Y1  - 2016
SN  - 978-1-5108-3800-0
SP  - 570
EP  - 577
ER  - 
TY  - CHAP
A1  - Weber, Tobias
A1  - Tellis, Jane J.
A1  - Duhovic, Miro
T1  - Characterization of tool-part-interaction an interlaminar friction for manufacturing process simulation
T2  - ECCM 17, 17th European Conference on Composite Materials, München, DE, Jun 26-30, 2016
Y1  - 2016
SN  - 978-3-00-053387-7
SP  - 1
EP  - 7
ER  - 
TY  - CHAP
A1  - Grundmann, Jan Thimo
A1  - Biele, Jens
A1  - Dachwald, Bernd
A1  - Grimm, Christian
A1  - Lange, Caroline
A1  - Ulamec, Stephan
T1  - Small spacecraft for small solar system body science, planetary defence and applications
T2  - IEEE Aerospace Conference 2016
N2  - 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.
Y1  - 2016
SP  - 1
EP  - 20
ER  - 
TY  - CHAP
A1  - Finger, Felix
T1  - Comparative Performance and Benefit Assessment of VTOL and CTOL UAVs
T2  - Deutscher Luft- und Raumfahrtkongress (DLRK) 2016, 13.-15.9.2016
Y1  - 2016
ER  - 
TY  - CHAP
A1  - Funke, Harald
A1  - Keinz, Jan
A1  - Kusterer, K.
A1  - Haj Ayed, A.
A1  - Kazari, M.
A1  - Kitajima, J.
A1  - Horikawa, A.
A1  - Okada, K.
T1  - Experimental and Numerical Study on Optimizing the DLN Micromix Hydrogen Combustion Principle for Industrial Gas Turbine Applications
T2  - ASME Turbo Expo 2015: Turbine Technical Conference and Exposition Volume 4A: Combustion, Fuels and Emissions Montreal, Quebec, Canada, June 15–19, 2015
Y1  - 2015
SN  - 978-0-7918-5668-0
U6  - https://doi.org/10.1115/GT2015-42043
SP  - V04AT04A008
ER  - 
TY  - CHAP
A1  - Theis, Jochen
A1  - Krisnamurthy, Hemanth Kumar
A1  - Schmitz, Günter
ED  - Jamal, Rahman
T1  - Modellbasierte Simulation und experimentelle Anwendung von mechatronischen Systemen in der Lehre in Verbindung mit NI myRIO und dem NI LabVIEW Interface Toolkit
T2  - Virtuelle Instrumente in der Praxis 2015 : Mess-, Steuer-, Regel- und Embedded-Systeme; Begleitband zum 20. VIP-Kongress
Y1  - 2015
SN  - 978-3-8007-3669-0
SP  - 362
EP  - 365
PB  - VDE-Verl.
CY  - Berlin
ER  - 
TY  - CHAP
A1  - Neu, Eugen
A1  - Janser, Frank
A1  - Khatibi, Akbar A.
A1  - Orifici, Adrian C.
T1  - Operational modal analysis of a cantilever in a wind tunnel using optical fiber bragg grating sensors
T2  - 6th International Operational Modal Analysis Conference. IOMAC´15. 2015 May 12-14 Gijon - Spain
Y1  - 2015
U6  - https://doi.org/10.13140/RG.2.1.3753.0324
ER  - 
TY  - CHAP
A1  - Horikawa, Atsushi
A1  - Okada, Kunio
A1  - Kazari, Masahide
A1  - Funke, Harald
A1  - Keinz, Jan
A1  - Kusterer, Karsten
A1  - Haj Ayed, Anis
T1  - Application of Low NOx Micro-Mix Hydrogen Combustion to Industrial Gas Turbine Combustor and Conceptual Design
T2  - Proceedings of International Gas Turbine Congress 2015 Tokyo November 15-20, 2015, Tokyo, Japan
Y1  - 2015
SN  - 978-4-89111-008-6
N1  - IGTC15-0238
SP  - 141
EP  - 146
ER  - 
TY  - CHAP
A1  - Funke, Harald
A1  - Keinz, Jan
A1  - Haj Ayed, A.
A1  - Kazari, M.
A1  - Kitajima, J.
A1  - Horikawa, A.
A1  - Okada, K.
T1  - Development and Testing of a Low NOx Micromix Combustion Chamber for an Industrial Gas Turbine
T2  - Proceedings of International Gas Turbine Congress 2015 Tokyo November 15-20, 2015, Tokyo, Japan
Y1  - 2015
SN  - 978-4-89111-008-6
N1  - IGTC15-0092
SP  - 131
EP  - 140
ER  - 
TY  - CHAP
A1  - Roosen, Petra
A1  - Feyerl, Günter
T1  - Gender-specific perception and utilization of personal use vehicles
T2  - FISITA World Automotive Congress 2014 : Maastricht, The Netherlands, 2 - 6 June / [organised by the International Federation of Automotive Engineering Societies (FISITA) ...]. Bd. 1
Y1  - 2015
SN  - 978-1-5108-0209-4
SP  - 418
EP  - 425
PB  - Curran
CY  - Red Hook, NY
ER  - 
TY  - CHAP
A1  - Horikawa, Atsushi
A1  - Kazari, Masahide
A1  - Okada, Kunio
A1  - Funke, Harald
A1  - Keinz, Jan
A1  - Kusterer, Karsten
A1  - Haji Ayed, Anis
T1  - Developments of Hydrogen Dry Low Emission Combustion Technology
T2  - Annual Congress of Gas Turbine Society Japan, 2015
Y1  - 2015
N1  - Abstract in engl.; Text in japanisch
ER  - 
TY  - CHAP
A1  - Grundmann, Jan Thimo
A1  - Lange, Caroline
A1  - Dachwald, Bernd
A1  - Grimm, Christian
A1  - Koch, Aaron
A1  - Ulamec, Stephan
T1  - Small Spacecraft in Planetary Defence Related Applications–Capabilities, Constraints, Challenges
T2  - IEEE Aerospace Conference
N2  - 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.
KW  - small spacecraft
KW  - planetary defence
KW  - asteroid lander
KW  - solar sail
KW  - flotilla missions
Y1  - 2015
N1  - 2015 IEEE Aerospace Conference, 7.-13. Mar. 2015, Big Sky, Montana, USA.
SP  - 1
EP  - 18
ER  - 
TY  - CHAP
A1  - Pirovano, Laura
A1  - Seefeldt, Patric
A1  - Dachwald, Bernd
A1  - Noomen, Ron
T1  - Attitude and Orbital Dynamics Modeling for an Uncontrolled Solar-Sail Experiment in Low-Earth Orbit
T2  - 25th International Symposium on Spaceflight Dynamics, 2015, Munich, Germany
Y1  - 2015
ER  - 
TY  - CHAP
A1  - Seefeldt, Patric
A1  - Bauer, Waldemar
A1  - Dachwald, Bernd
A1  - Grundmann, Jan Thimo
A1  - Straubel, Marco
A1  - Sznajder, Maciej
A1  - Tóth, Norbert
A1  - Zander, Martin E.
T1  - Large lightweight deployable structures for planetary defence: solar sail propulsion, solar concentrator payloads, large-scale photovoltaic power
T2  - 4th IAA Planetary Defense Conference - PDC 2015, 13-17 April 2015, Frascati, Roma, Italy
Y1  - 2015
N1  - IAA-PDC-15-P-20
ER  - 
TY  - CHAP
A1  - Weber, Tobias
A1  - Englhard, Markus
A1  - Hailer, Benjamin
A1  - Arent, Jan-Christoph
T1  - Manufacturing Process Simulation for the Prediction of Tool-Part-Interaction and Ply Wrinkling
T2  - Proceedings of SAMPE Europe Conference, Amiens , France
Y1  - 2015
SP  - 1
EP  - 10
ER  - 
TY  - CHAP
A1  - Weber, Tobias
T1  - Manufacturing Process Simulation for Tooling Optimization: Reduction of Quality Issues During Autoclave Manufacturing of Composite Parts
T2  - Proceedings of SAMPE Europe Conference 2015, Amiens, France
Y1  - 2015
SP  - 1
EP  - 8
ER  - 
TY  - CHAP
A1  - Otten, D.
A1  - Schmid, M.
A1  - Weber, Tobias
T1  - Advances In Sheet Metal-Forming: Reduction Of Tooling Cost By Methodical Optimization
T2  - Proceedings of SAMPE Europe Conference, Amiens , France
Y1  - 2015
ER  - 
TY  - CHAP
A1  - Peloni, Alessandro
A1  - Ceriotti, Matteo
A1  - Dachwald, Bernd
T1  - Solar-Sailing Trajectory Design for Close-up NEA Observations Mission
T2  - 4th IAA Planetary Defense Conference - PDC 2015, 13-17 April 2015, Frascati, Roma, Italy
Y1  - 2015
N1  - IAA-PDC-15-P-19
ER  - 
TY  - CHAP
A1  - Peloni, A.
A1  - Ceriotti, M.
A1  - Dachwald, Bernd
T1  - Preliminary trajectory design of a multiple NEO rendezvous mission through solar sailing
T2  - Proceedings of the International Astronautical Congress, IAC, Vol. 8, 2014
Y1  - 2015
SN  - 978-1-63439-986-9
SP  - 5352
EP  - 5366
PB  - Curran
CY  - Red Hook, NY
ER  - 
TY  - CHAP
A1  - Grundmann, Jan Thimo
A1  - Bauer, Waldemar
A1  - Biele, Jens
A1  - Cordero, Frederico
A1  - Dachwald, Bernd
A1  - Koncz, Alexander
A1  - Krause, Christian
A1  - Mikschl, Tobias
A1  - Montenegro, Sergio
A1  - Quantius, Dominik
A1  - Ruffer, Michael
A1  - Sasaki, Kaname
A1  - Schmitz, Nicole
A1  - Seefeldt, Patric
A1  - Tóth, Norbert
A1  - Wejmo, Elisabet
T1  - From Sail to Soil – Getting Sailcraft Out of the Harbour on a Visit to One of Earth’s Nearest Neighbours
T2  - 4th IAA Planetary Denfense Conference - PDC 2015,  13-17 April 2015, Frascati, Roma, Italy
Y1  - 2015
ER  - 
TY  - CHAP
A1  - Pirovano, Laura
A1  - Seefeldt, Patric
A1  - Dachwald, Bernd
A1  - Noomen, Ron
T1  - Attitude and orbital modeling of an uncontrolled solar-sail experiment in low-Earth orbit
T2  - 25th International Symposium on Space Flight Dynamics ISSFD
N2  - 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
KW  - Solar sail
KW  - Gossamer structures
KW  - Attitude dynamics
KW  - Orbital dynamics
Y1  - 2015
N1  - 25th International Symposium on Space Flight Dynamics ISSFD
October 19 – 23, 2015, Munich, Germany
https://issfd.org/2015/
SP  - 1
EP  - 15
ER  - 
TY  - CHAP
A1  - Konstantinidis, K.
A1  - Kowalski, Julia
A1  - Martinez, C. F.
A1  - Dachwald, Bernd
A1  - Ewerhart, D.
A1  - Förstner, R.
T1  - Some necessary technologies for in-situ astrobiology on enceladus
T2  - Proceedings of the International Astronautical Congress
Y1  - 2015
SN  - 978-151081893-4
N1  - 6th International Astronautical Congress 2015: Space - The Gateway for Mankind's Future, IAC 2015; Jerusalem; Israel; 12 October 2015 through 16 October 2015
SP  - 1354
EP  - 1372
ER  - 
TY  - CHAP
A1  - Schirra, Julian
A1  - Watmuff, Jon
A1  - Bauschat, J.-Michael
T1  - A relative assessment of existing potential-methodologies to accurately estimate the induced drag of highly non-planar lifting systems
T2  - Advanced aero concepts, design and operations : Applied Aerodynamics Conference  : July 22 -24, 2014, Bristol, UK
Y1  - 2014
SP  - 1
EP  - 13
ER  - 
TY  - CHAP
A1  - Schirra, Julian
A1  - Bauschat, J.-Michael
A1  - Watmuff, J.H.
T1  - Accurate induced drag prediction for highly non-planar lifting systems
T2  - 19th Australasian Fluid Mechanics Conference : 8.-11. Dezember 2014, Melbourne, Australia
N2  - The impact of wake model effects is investigated for two highly
non-planar lifting systems. Dependent on the geometrical
arrangement of the configuration, the wake model shape is found
to considerably affect the estimation. Particularly at higher angles
of attack, an accurate estimation based on the common linear wake
model approaches is involved.
Y1  - 2014
ER  - 
TY  - CHAP
A1  - Funke, Harald
A1  - Haj Ayed, A.
A1  - Kusterer, K.
A1  - Keinz, Jan
A1  - Kazari, M.
A1  - Kitajima, J.
A1  - Horikawa, A.
A1  - Okada, K.
T1  - Numerical Study on Increased Energy Density for the DLN Micromix Hydrogen Combustion Principle
T2  - Combustion, Fuels and Emissions (ASME Turbo Expo 2014: Turbine Technical Conference and Exposition : Düsseldorf, Germany, June 16–20, 2014 ; Vol. 4A)
Y1  - 2014
SN  - 978-0-7918-4568-4
N1  - Paper No. GT2014-25848
SP  - V04AT04A057
PB  - ASME
CY  - New York, N.Y.
ER  - 
TY  - CHAP
A1  - Niedermeier, H.
A1  - Clemens, J.
A1  - Kowalski, Julia
A1  - Macht, S.
A1  - Heinen, D.
A1  - Hoffmann, R.
A1  - Linder, Peter
T1  - Navigation system for a research ice probe for antarctic glaciers
T2  - IEEE/ION Position, Location and Navigation Symposium (PLANS) ; 5-8 May 2014, Monterey, Calif.
Y1  - 2014
SN  - 978-1-4799-3319-8
SP  - 959
EP  - 975
PB  - IEEE
CY  - Piscataway, NJ
ER  - 
TY  - CHAP
A1  - Funke, Harald
A1  - Börner, Sebastian
A1  - Hendrick, P.
A1  - Recker, E.
A1  - Elsing, R.
ED  - DeLuca, Luigi T.
T1  - Development and integration of a scalable low NOx combustion chamber for a hydrogen fuelled aero gas turbine
T2  - Progress in Propulsion Physics. - Vol. 4
Y1  - 2013
SN  - 978-2-7598-0876-2
U6  - https://doi.org/10.1051/eucass/201304357
N1  - 4th European Conference for Aero-Space Sciences : July 4 - 8, 2011, St Petersburg, Russia ; EUCASS <4, 2011, St. Petersburg>
SP  - 357
EP  - 372
PB  - EDP Sciences
CY  - [Les Ulis]
ER  - 
TY  - CHAP
A1  - Spohr, A.
A1  - Schirra, Julian
A1  - Hoefling, J.
A1  - Schedl, A.
T1  - Wing weight estimation methodology for highly non-planar lifting systems during conceptual design
T2  - Deutscher Luft- und Raumfahrtkongress 2013 : 10.9. - 12.9.2013, Stuttgart
Y1  - 2013
SP  - Publ. online
ER  - 
TY  - CHAP
A1  - Hoefling, J.
A1  - Schirra, Julian
A1  - Spohr, A.
A1  - Schäfer, D.
T1  - Induced drag computation with wake model schemes for highly non-planar wing systems
T2  - Deutscher Luft- und Raumfahrtkongress 2013 : 10.9. - 12.9.2013, Stuttgart
Y1  - 2013
SP  - 1
EP  - 10
PB  - Dt. Ges. für Luft- und Raumfahrt
CY  - Bonn
ER  - 
TY  - CHAP
A1  - Funke, Harald
A1  - Keinz, Jan
A1  - Börner, Sebastian
A1  - Haj Ayed, A.
A1  - Kusterer, K.
A1  - Tekin, N.
A1  - Kazari, M.
A1  - Kitajima, J.
A1  - Horikawa, A.
A1  - Okada, K.
ED  - Song, Seung Jin
T1  - Experimental and numerical characterization of the dry low NOx micromix hydrogen combustion principle at increased energy density for industrial hydrogen gas turbine applications
T2  - Combustion, fuels and emissions : proceedings of the ASME Turbo Expo: Turbine Technical Conference and Exposition - 2013 ; June 3 - 7, 2013, San Antonio, Texas, USA ; vol. 1
Y1  - 2013
SN  - 978-0-7918-5510-2
N1  - Paper No: GT2013-94771
SP  - V001T04A055
PB  - ASME
CY  - New York, NY
ER  - 
TY  - CHAP
A1  - Schirra, Julian
A1  - J., Watmuff
T1  - Euler-based induced drag estimation for highly non-planar lifting systems during conceptional design
T2  - 62. Deutscher Luft- und Raumfahrtkongress 2013 : 10. - 12. September 2032, Stuttgart, Haus der Wirtschaft
Y1  - 2013
SP  - 1
EP  - 8
PB  - Dt. Gesellschaft für Luft- und Raumfahrt
CY  - Bonn
ER  - 
TY  - CHAP
A1  - Konstantinidis, K.
A1  - Dachwald, Bernd
A1  - Ohndorf, A.
A1  - Dykta, P.
A1  - Voigt, K.
A1  - Förstner, R.
T1  - Enceladus explorer (ENEX): A lander mission to probe subglacial water pockets on Saturn's moon enceladus for life
T2  - 64th International Astronautical Congress 2013 (IAC 2013) : Beijing, China, 23 - 27 September 2013. (Proceedings of the International Astronautical Congress, IAC ; 2)
Y1  - 2013
SN  - 978-1-62993-909-4
SP  - 1340
EP  - 1350
PB  - Curran
CY  - Red Hook, NY
ER  - 
TY  - CHAP
A1  - Gierse, Andreas
A1  - Krämer, Stefan
A1  - Daab, Dominique J.
A1  - Hessel, Joana
A1  - Baader, Fabian
A1  - Müller, Brigitte S.
A1  - Wagner, Tobias
A1  - Gdalewitsch, Georg
A1  - Plescher, Engelbert
A1  - Pfützenreuter, Lysan
T1  - Experimental in-flight modal-analysis of a sounding rocket structure
T2  - 21st ESA Symposium on Rocket and Ballon related Research
Y1  - 2013
SN  - 9789290922858
SP  - 341
EP  - 346
ER  - 
TY  - CHAP
A1  - Duprat, J.
A1  - Dachwald, Bernd
A1  - Hilchenbach, M.
A1  - Engrand, Cecile
A1  - Espe, C.
A1  - Feldmann, M.
A1  - Francke, Gero
A1  - Görög, Mark
A1  - Lüsing, N.
A1  - Langenhorst, Falko
T1  - The MARVIN project: a micrometeorite harvester in Antarctic snow
T2  - 44th Lunar and Planetary Science Conference
N2  - MARVIN is an automated drilling and melting probe dedicated to collect pristine interplanetary dust particles (micrometeorites) from central Antarctica snow.
Y1  - 2013
N1  - 44th Lunar and Planetary Science Conference, March 18-22, 2013, The Woodlands, Texas
ER  - 
TY  - CHAP
A1  - Funke, Harald
A1  - Börner, Sebastian
A1  - Keinz, Jan
A1  - Kusterer, K.
A1  - Kroninger, D.
A1  - Kitajima, J.
A1  - Kazari, M.
A1  - Horikama, A.
T1  - Numerical and experimental characterization of low NOx Micromix combustion principle for industrial hydrogen gas turbine applications
T2  - Proceedings of ASME Turbo Expo 2012
Y1  - 2013
N1  - ASME Turbo Expo 2012, GT2012, June 11-15, 2012, Copenhagen, Denmark
ER  - 
TY  - CHAP
A1  - Funke, Harald
A1  - Börner, Sebastian
A1  - Keinz, Jan
A1  - Hendrick, P.
A1  - Recker, E.
T1  - Low NOx Hydrogen combustion chamber for industrial gas turbine applications“, 14th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery
T2  - ISROMAC-14 : the Forteenth International Symposium on Transport Phenomena and Dynamics of Rotating Machinery ; Honolulu, Hawaii, February 27 - March 02nd, 2012
Y1  - 2012
N1  - International Symposium on Transport Phenomena and Dynamics of Rotating Machinery ; (14 ; 2012.02.27-03.02 ; Honolulu, Hawaii)
ER  - 
TY  - CHAP
A1  - Dachwald, Bernd
A1  - Feldmann, Marco
A1  - Espe, Clemens
A1  - Plescher, Engelbert
A1  - Konstantinidis, K.
A1  - Forstner, R.
T1  - Enceladus explorer - A maneuverable subsurface probe for autonomous navigation through deep ice
T2  - 63rd International Astronautical Congress 2012, IAC 2012; Naples; Italy; 1 October 2012 through 5 October 2012. (Proceedings of the International Astronautical Congress, IAC ; 3)
Y1  - 2012
SN  - 978-1-62276-979-7
SP  - 1756
EP  - 1766
PB  - Curran
CY  - Red Hook, NY
ER  - 
TY  - CHAP
A1  - Knobloch, V.
A1  - Kowalski, Julia
A1  - Bösiger, P.
A1  - Kozerke, S.
T1  - Probabilistic Streamline Estimation from Accelerated Fourier Velocity Encoded Measurements
T2  - Proceedings of the 19th ISMRM International Society for Magnetic Resonance in Medicine
Y1  - 2011
N1  - ISMRM 19th Annual Meeting & Exhibition in Montréal, Québec, Canada
SP  - 1215
EP  - 1215
ER  - 
TY  - CHAP
A1  - Olaru, Alexandra Maria
A1  - Kowalski, Julia
A1  - Sethi, Vaishali
A1  - Blümich, Bernhard
T1  - Fluid Transport in Porous Media probed by Relaxation-Exchange NMR
T2  - 2011 Fall Meeting, AGU, San Francisco, Calif., 5-9 Dec.
Y1  - 2011
N1  - H12B-07; American Geophysical Union
ER  - 
TY  - CHAP
A1  - Ohndorf, Andreas
A1  - Dachwald, Bernd
A1  - Seboldt, Wolfgang
A1  - Schartner, Karl-Heinz
T1  - Flight times to the heliopause using a combination of solar and radioisotope electric propulsion
T2  - 32nd International Electric Propulsion Conference
N2  - 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".
KW  - low-thrust trajectory optimization
KW  - heliosphere
KW  - ion propulsion
Y1  - 2011
N1  - IEPC-2011-051
32nd International Electric Propulsion Conference,September 11–15, 2011
Wiesbaden, Germany
SP  - 1
EP  - 12
ER  - 
TY  - CHAP
A1  - Loeb, Horst W.
A1  - Schartner, Karl-Heinz
A1  - Dachwald, Bernd
A1  - Ohndorf, Andreas
A1  - Seboldt, Wolfgang
T1  - An Interstellar – Heliopause mission using a combination of solar/radioisotope electric propulsion
T2  - Presented at the 32nd International Electric Propulsion Conference
N2  - 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.
Y1  - 2011
N1  - 32nd International Electric Propulsion Conference, 11-15 September. Wiesbaden, Germany
SP  - 1
EP  - 7
ER  -