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  - http://dx.doi.org/10.1007/978-981-19-3179-6_55
SN  - 2195-4356
N1  - The 7th International Conference and Exhibition on Sustainable Energy and Advanced Material (ICE-SEAM 2021) was organized by Universiti Teknikal Malaysia Melaka (UTeM), Malaysia, in association with the Universitas Sebelas Maret (UNS), Indonesia, on 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  - 
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  - http://dx.doi.org/10.2514/6.2018-5005
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  - Horikawa, Atsushi
A1  - Ashikaga, Mitsugu
A1  - Yamaguchi, Masato
A1  - Ogino, Tomoyuki
A1  - Aoki, Shigeki
A1  - Wirsum, Manfred
A1  - Funke, Harald
A1  - Kusterer, Karsten
T1  - Combined heat and power supply demonstration of Micro-Mix Hydrogen Combustion Applied to M1A-17 Gas Turbine
T2  - Proceedings of ASME Turbo Expo 2022: Turbomachinery Technical Conference and Exposition (GT2022) (Volume 3A)
N2  - Kawasaki Heavy Industries, Ltd. (KHI), Aachen University of Applied Sciences, and B&B-AGEMA GmbH have investigated the potential of low NOx micro-mix (MMX) hydrogen combustion and its application to an industrial gas turbine combustor. Engine demonstration tests of a MMX combustor for the M1A-17 gas turbine with a co-generation system were conducted in the hydrogen-fueled power generation plant in Kobe City, Japan.
This paper presents the results of the commissioning test and the combined heat and power (CHP) supply demonstration. In the commissioning test, grid interconnection, loading tests and load cut-off tests were successfully conducted. All measurement results satisfied the Japanese environmental regulation values. Dust and soot as well as SOx were not detected. The NOx emissions were below 84 ppmv at 15 % O2. The noise level at the site boundary was below 60 dB. The vibration at the site boundary was below 45 dB.
During the combined heat and power supply demonstration, heat and power were supplied to neighboring public facilities with the MMX combustion technology and 100 % hydrogen fuel. The electric power output reached 1800 kW at which the NOx emissions were 72 ppmv at 15 % O2, and 60 %RH. Combustion instabilities were not observed. The gas turbine efficiency was improved by about 1 % compared to a non-premixed type combustor with water injection as NOx reduction method. During a total equivalent operation time of 1040 hours, all combustor parts, the M1A-17 gas turbine as such, and the co-generation system were without any issues.
KW  - industrial gas turbine
KW  - combustor development
KW  - fuels
KW  - hydrogen
KW  - emission
Y1  - 2022
SN  - 978-0-7918-8599-4
U6  - http://dx.doi.org/10.1115/GT2022-81620
N1  - ASME Turbo Expo 2022: Turbomachinery Technical Conference and Exposition
June 13–17, 2022 Rotterdam, Netherlands
PB  - American Society of Mechanical Engineers
CY  - Fairfield
ER  - 
TY  - CHAP
A1  - Horikawa, Atsushi
A1  - Okada, Kunio
A1  - Yamaguchi, Masato
A1  - Aoki, Shigeki
A1  - Wirsum, Manfred
A1  - Funke, Harald
A1  - Kusterer, Karsten
T1  - Combustor development and engine demonstration of micro-mix hydrogen combustion applied to M1A-17 gas turbine
T2  - ASME Turbo Expo 2021: Turbomachinery Technical Conference and Exposition // Volume 3B: Combustion, Fuels, and Emissions
N2  - Kawasaki Heavy Industries, LTD. (KHI) has research and development projects for a future hydrogen society. These projects comprise the complete hydrogen cycle, including the production of hydrogen gas, the refinement and liquefaction for transportation and storage, and finally the utilization in a gas turbine for electricity and heat supply. Within the development of the hydrogen gas turbine, the key technology is stable and low NOx hydrogen combustion, namely the Dry Low NOx (DLN) hydrogen combustion.

KHI, Aachen University of Applied Science, and B&B-AGEMA have investigated the possibility of low NOx micro-mix hydrogen combustion and its application to an industrial gas turbine combustor. From 2014 to 2018, KHI developed a DLN hydrogen combustor for a 2MW class industrial gas turbine with the micro-mix technology. Thereby, the ignition performance, the flame stability for equivalent rotational speed, and higher load conditions were investigated. NOx emission values were kept about half of the Air Pollution Control Law in Japan: 84ppm (O2-15%). Hereby, the elementary combustor development was completed.

From May 2020, KHI started the engine demonstration operation by using an M1A-17 gas turbine with a co-generation system located in the hydrogen-fueled power generation plant in Kobe City, Japan. During the first engine demonstration tests, adjustments of engine starting and load control with fuel staging were investigated. On 21st May, the electrical power output reached 1,635 kW, which corresponds to 100% load (ambient temperature 20 °C), and thereby NOx emissions of 65 ppm (O2-15, 60 RH%) were verified. Here, for the first time, a DLN hydrogen-fueled gas turbine successfully generated power and heat.
KW  - industrial gas turbine
KW  - combustor development
KW  - engine demonstration
KW  - fuels
KW  - hydrogen
Y1  - 2021
U6  - http://dx.doi.org/10.1115/GT2021-59666
N1  - ASME Turbo Expo 2021: Turbomachinery Technical Conference and Exposition. June 7–11, 2021. Virtual, Online.

Paper No: GT2021-59666, V03BT04A014
ER  - 
TY  - CHAP
A1  - Finger, Felix
A1  - Braun, Carsten
A1  - Bil, Cees
T1  - Comparative assessment of parallel-hybrid-electric propulsion systems for four different aircraft
T2  - AIAA SciTech Forum 2020, 06.01.2020 - 10.01.2020, Orlando
Y1  - 2020
U6  - http://dx.doi.org/10.2514/6.2020-1502
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  - Reimer, Lars
A1  - Braun, Carsten
A1  - Chen, B.-H.
A1  - Ballmann, Josef
T1  - Computational aeroelastic analysis and design of the HIRENASD wind tunnel wing model and tests
T2  - Proceedings / IFASD 2007, CEAS/AIAA/KTH International Forum on Aeroelasticity and Structural Dynamics : June 18 - 21, 2007, Stockholm, Sweden
Y1  - 2007
PB  - KTH
CY  - Stockholm
ER  - 
TY  - CHAP
A1  - Kemper, Hans
A1  - Hellenbroich, Gereon
A1  - Esch, Thomas
T1  - Concept of an innovative passenger-car hybrid drive for European driving conditions
T2  - Hybrid vehicles and energy management : 6th symposium ; 18th and 19th February 2009, Stadthalle Braunschweig
N2  - The downsizing of spark ignition engines in conjunction with turbocharging is considered to be a promising method for reducing CO₂ emissions. Using this concept, FEV has developed a new, highly efficient drivetrain to demonstrate fuel consumption reduction and drivability in a vehicle based on the Ford Focus ST. The newly designed 1.8L turbocharged gasoline engine incorporates infinitely variable intake and outlet control timing and direct fuel injection utilizing piezo injectors centrally located. In addition, this engine uses a prototype FEV engine control system, with software that was developed and adapted entirely by FEV. The vehicle features a 160 kW engine with a maximum mean effective pressure of 22.4 bar and 34 % savings in simulated fuel consumption. During the first stage, a new electrohydraulically actuated hybrid transmission with seven forward gears and one reverse gear and a single dry starting clutch will be integrated. The electric motor of the hybrid is directly connected to the gear set of the transmission. Utilizing the special gear set layout, the electric motor can provide boost during a change of gears, so that there is no interruption in traction. Therefore, the transmission system combines the advantages of a double clutch controlled gear change (gear change without an interruption in traction) with the efficient, cost-effective design of an automated manual transmission system. Additionally, the transmission provides a purely electric drive system and the operation of an air-conditioning compressor during the engine stop phases. One other alternative is through the use of CAI (Controlled Auto Ignition), which incorporates a process developed by FEV for controlled compression ignition.
Y1  - 2009
SN  - 978-3-937655-20-8
SP  - 264
EP  - 287
PB  - Gesamtzentrum für Verkehr (GZVB)
CY  - Braunschweig
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  - 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  -