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  - 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  - Nowack, N.
A1  - Röth, Thilo
A1  - Bührig-Polaczek, A.
A1  - Klaus, G.
ED  - Hirsch, Jürgen
T1  - Advanced Sheet Metal Components Reinforced by Light Metal Cast Structures
T2  - Aluminium alloys : their physical and mechanical properties ; [proceedings of the 11th International Conference on Aluminium Alloys, 22 - 26 Sept. 2008, Aachen, Germany ; ICAA 11]
Y1  - 2008
SN  - 978-3-527-32367-8
IS  - 2
SP  - 2374
EP  - 2381
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  - 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  - Geiben, Benedikt
A1  - Götten, Falk
A1  - Havermann, Marc
T1  - Aerodynamic analysis of a winged sub-orbital spaceplane
N2  - This paper primarily presents an aerodynamic CFD analysis of a winged spaceplane geometry based on the Japanese Space Walker proposal. StarCCM was used to calculate aerodynamic coefficients for a typical space flight trajectory including super-, trans- and subsonic Mach numbers and two angles of attack. Since the solution of the RANS equations in such supersonic flight regimes is still computationally expensive, inviscid Euler simulations can principally lead to a significant reduction in computational effort. The impact on accuracy of aerodynamic properties is further analysed by comparing both methods for different flight regimes up to a Mach number of 4.
Y1  - 2020
U6  - https://doi.org/10.25967/530170
N1  - 69. Deutscher Luft- und Raumfahrtkongress 2020, 1. September 2020 - 3. September 2020, online
PB  - DGLR
CY  - Bonn
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  - Kowalski, Julia
A1  - Bugnion, Louis
T1  - An extended shallow flow theory for natural debris flows
Y1  - 2009
N1  - 2009 Portland GSA Annual Meeting (18-21 October 2009); Geological Society of America
VL  - 41
IS  - 7
SP  - 609
EP  - 609
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  - 
TY  - CHAP
A1  - Reimer, Lars
A1  - Braun, Carsten
A1  - Ballmann, Josef
T1  - Analysis of the static and dynamic aero-structural response of an elastic swept wing model by direct aeroelastic simulation
T2  - ICAS 2006 proceedings : 25th Congress of the International Council of the Aeronautical Sciences ; Hamburg, Germany, 3 - 8 September, 2006 : 25th International Congress of Aeronautical Sciences
Y1  - 2006
SN  - 0-9533991-7-6
SP  - Paper No. 2006-10.3.3
PB  - Optimage
CY  - Edinburgh
ER  - 
TY  - CHAP
A1  - Gehler, M.
A1  - Ober-Blöbaum, S.
A1  - Dachwald, Bernd
T1  - Application of discrete mechanics and optimal control to spacecraft in non-keplerian motion around small solar system bodies
T2  - Procceedings of the 60th International Astronautical Congress
N2  - Prolonged operations close to small solar system bodies require a sophisticated control logic to minimize propellant mass and maximize operational efficiency. A control logic based on Discrete Mechanics and Optimal Control (DMOC) is proposed and applied to both conventionally propelled and solar sail spacecraft operating at an arbitrarily shaped asteroid in the class of Itokawa. As an example, stand-off inertial hovering is considered, recently identified as a challenging part of the Marco Polo mission. The approach is easily extended to stand-off orbits. We show that DMOC is applicable to spacecraft control at small objects, in particular with regard to the fact that the changes in gravity are exploited by the algorithm to optimally control the spacecraft position. Furthermore, we provide some remarks on promising developments.
KW  - Spacecraft
Y1  - 2009
SN  - 978-161567908-9
N1  - 60th International Astronautical Congress 2009, IAC 2009; Daejeon; South Korea; 12 October 2009 through 16 October 2009
SP  - 1360
EP  - 1371
PB  - Elsevier
CY  - Amsterdam
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  - 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  - 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  - 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  - Pflug, J.
A1  - Wahle, Michael
ED  - Bürger, Gudrun
T1  - Auslegung der CFK-Sandwich-Rumpfstruktur eines Hubschraubers mit der Methode der Finiten Elemente
T2  - Basistechnologien für neue Herausforderungen in der Luft- und Raumfahrt : DGLR-Jahrestagung / Deutscher Luft- und Raumfahrt-Kongress 1994, Erlangen, 04.- 07. Oktober 1994. - (Jahrbuch der Deutschen Gesellschaft für Luft- und Raumfahrt ; 1994,3)
Y1  - 1994
SP  - 1135
EP  - 1144
PB  - DGLR
CY  - Bonn
ER  - 
TY  - CHAP
A1  - Veettil, Yadu Krishna Morassery
A1  - Rakshit, Shantam
A1  - Schopen, Oliver
A1  - Kemper, Hans
A1  - Esch, Thomas
A1  - Shabani, Bahman
ED  - Bin Abdollah, Mohd Fadzli
ED  - Amiruddin, Hilmi
ED  - Singh, Amrik Singh Phuman
ED  - Munir, Fudhail Abdul
ED  - Ibrahim, Asriana
T1  - Automated Control System Strategies to Ensure Safety of PEM Fuel Cells Using Kalman Filters
T2  - Proceedings of the 7th International Conference and Exhibition on Sustainable Energy and Advanced Materials (ICE-SEAM 2021), Melaka, Malaysia
N2  - Having well-defined control strategies for fuel cells, that can efficiently detect errors and take corrective action is critically important for safety in all applications, and especially so in aviation. The algorithms not only ensure operator safety by monitoring the fuel cell and connected components, but also contribute to extending the health of the fuel cell, its durability and safe operation over its lifetime. While sensors are used to provide peripheral data surrounding the fuel cell, the internal states of the fuel cell cannot be directly measured. To overcome this restriction, Kalman Filter has been implemented as an internal state observer.
Other safety conditions are evaluated using real-time data from every connected sensor and corrective actions automatically take place to ensure safety. The algorithms discussed in this paper have been validated thorough Model-in-the-Loop (MiL) tests as well as practical validation at a dedicated test bench.
KW  - control system
KW  - PEM fuel cells
KW  - Kalman filter
Y1  - 2022
SN  - 978-981-19-3178-9
SN  - 978-981-19-3179-6 (E-Book)
U6  - https://doi.org/10.1007/978-981-19-3179-6_55
SN  - 2195-4356
N1  - 7th International Conference and Exhibition on Sustainable Energy and Advanced Material (ICE-SEAM 2021), Universiti Teknikal Malaysia Melaka (UTeM), Malaysia, in association with the Universitas Sebelas Maret (UNS), Indonesia, 23 November 2021
SP  - 296
EP  - 299
PB  - Springer Nature
CY  - Singapore
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  - Christen, Marc
A1  - Bartelt, Perry
A1  - Kowalski, Julia
A1  - Stoffel, Lukus
T1  - Calculation of dense snow avalanches in three-dimensional terrain with the numerical simulation programm RAMMS
T2  - Proceedings ISSW 2008 ; International Snow Science Workshop. Whistler 2008
N2  - Numerical models have become an essential part of snow avalanche engineering. Recent
advances in understanding the rheology of flowing snow and the mechanics of entrainment and
deposition have made numerical models more reliable. Coupled with field observations and historical
records, they are especially helpful in understanding avalanche flow in complex terrain. However, the
application of numerical models poses several new challenges to avalanche engineers. A detailed
understanding of the avalanche phenomena is required to specify initial conditions (release zone
dimensions and snowcover entrainment rates) as well as the friction parameters, which are no longer
based on empirical back-calculations, rather terrain roughness, vegetation and snow properties. In this
paper we discuss these problems by presenting the computer model RAMMS, which was specially
designed by the SLF as a practical tool for avalanche engineers. RAMMS solves the depth-averaged
equations governing avalanche flow with first and second-order numerical solution schemes. A
tremendous effort has been invested in the implementation of advanced input and output features.
Simulation results are therefore clearly and easily visualized to simplify their interpretation. More
importantly, RAMMS has been applied to a series of well-documented avalanches to gauge model
performance. In this paper we present the governing differential equations, highlight some of the input
and output features of RAMMS and then discuss the simulation of the Gatschiefer avalanche that
occurred in April 2008, near Klosters/Monbiel, Switzerland.
KW  - snow
KW  - avalanche
Y1  - 2008
SP  - 709
EP  - 716
ER  - 
TY  - CHAP
A1  - Wahle, Michael
T1  - Calculation of the response of heat exchanger tubes with regard to nonlinear and prestressing effects
T2  - Vibration in nuclear plant : proceedings of the 3rd International Conference on Vibration in Nuclear Plant held on 11 - 14 May 1982, Keswick ; vol. 1
Y1  - 1983
SN  - 0-7277-0192-4 (Druckausg.)
SN  - 978-0-7277-5270-3 (E-Book)
N1  - International Conference on Vibration in Nuclear Plant <3, 1982, Keswick>
N1  - Paper 1.10 (Log No. 71)
SP  - 162
EP  - 183
PB  - British Nuclear Energy Society
CY  - London
ER  -