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  - 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  - 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  - 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  - 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  - 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  - Adams, Moritz
A1  - Losekamm, Martin J.
A1  - Czupalla, Markus
T1  - Development of the Thermal Control System for the RadMap Telescope Experiment on the International Space Station
T2  - International Conference on Environmental Systems
Y1  - 2020
N1  - 2020 International Conference on Environmental Systems, 12. Juli 2020 – 16. Juli 2020, Lissabon
SP  - 1
EP  - 10
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  - 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  - 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  - 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  - Kreyer, Jörg
A1  - Müller, Marvin
A1  - Esch, Thomas
T1  - A Map-Based Model for the Determination of Fuel Consumption for Internal Combustion Engines as a Function of Flight Altitude
N2  - In addition to very high safety and reliability requirements, the design of internal combustion engines (ICE) in aviation focuses on economic efficiency. The objective must be to design the aircraft powertrain optimized for a specific flight mission with respect to fuel consumption and specific engine power. Against this background, expert tools provide valuable decision-making assistance for the customer. In this paper, a mathematical calculation model for the fuel consumption of aircraft ICE is presented. This model enables the derivation of fuel consumption maps for different engine configurations. Depending on the flight conditions and based on these maps, the current and the integrated fuel consumption for freely definable flight emissions is calculated. For that purpose, an interpolation method is used, that has been optimized for accuracy and calculation time. The mission boundary conditions flight altitude and power requirement of the ICE form the basis for this calculation. The mathematical fuel consumption model is embedded in a parent program. This parent program presents the simulated fuel consumption by means of an example flight mission for a representative airplane. The focus of the work is therefore on reproducing exact consumption data for flight operations. By use of the empirical approaches according to Gagg-Farrar [1] the power and fuel consumption as a function of the flight altitude are determined. To substantiate this approaches, a 1-D ICE model based on the multi-physical simulation tool GT-Suite® has been created. This 1-D engine model offers the possibility to analyze the filling and gas change processes, the internal combustion as well as heat and friction losses for an ICE under altitude environmental conditions. Performance measurements on a dynamometer at sea level for a naturally aspirated ICE with a displacement of 1211 ccm used in an aviation aircraft has been done to validate the 1-D ICE model. To check the plausibility of the empirical approaches with respect to the fuel consumption and performance adjustment for the flight altitude an analysis of the ICE efficiency chain of the 1-D engine model is done. In addition, a comparison of literature and manufacturer data with the simulation results is presented.
Y1  - 2020
U6  - https://doi.org/10.25967/490162
N1  - 68. Deutscher Luft- und Raumfahrtkongress 30.09.-02.10.2019, Darmstadt
PB  - DGLR
CY  - Bonn
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  - Englhard, Markus
A1  - Weber, Tobias
A1  - Arent, Jan-Christoph
T1  - Efficiency enhancement for CFRP-Prepregautoclave manufacturing by means of simulation-assisted loading optimization
T2  - Proceedings of SAMPE Europe Conference 2021
N2  - A new method for improved autoclave loading within the restrictive framework of helicopter manufacturing is proposed. It is derived from experimental and numerical studies of the curing process and aims at optimizing tooling positions in the autoclave for fast and homogeneous heat-up. The mold positioning is based on two sets of information. The thermal properties of the molds, which can be determined via semi-empirical thermal simulation. The second information is a previously determined distribution of heat transfer coefficients inside the autoclave. Finally, an experimental proof of concept is performed to show a cycle time reduction of up to 31% using the proposed methodology.
Y1  - 2021
N1  - SAMPE Europe Conference 2021, Baden/Zürich, Schweiz, 29. bis 30. September 2021
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  -