TY  - JOUR
A1  - Finger, Felix
T1  - Senkrechtstarter: FH-Absolvent wird für Transportdrohne ausgezeichnet
JF  - campushunter: das etwas andere Karrieremagazin - Wintersemester 16/17
Y1  - 2016
SN  - 2196-9426
IS  - 17. Regionalausgabe Aachen
SP  - 116
EP  - 117
PB  - Campushunter Media
CY  - Heidelberg
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  - 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 Parallel Hybrid Propulsion Systems
T2  - Deutscher Luft- und Raumfahrtkongress 2018
Y1  - 2018
U6  - http://dx.doi.org/10.25967/480227
ER  - 
TY  - JOUR
A1  - Götten, Falk
A1  - Finger, Felix
A1  - Havermann, Marc
A1  - Braun, Carsten
A1  - Gomez, Francisco
A1  - Bill, C.
T1  - On the flight performance impact of landing gear drag reduction methods for unmanned air vehicles
JF  - Deutscher Luft- und Raumfahrtkongress 2018
N2  - The flight performance impact of three different landing gear configurations on a small, fixed-wing UAV is analyzed with a combination of RANS CFD calculations and an incremental flight performance algorithm. A standard fixed landing gear configuration is taken as a baseline, while the influence of retracting the landing gear or applying streamlined fairings is investigated. A retraction leads to a significant parasite drag reduction, while also fairings promise large savings. The increase in lift-to-drag ratio is reduced at high lift coefficients due to the influence of induced drag. All configurations are tested on three different design missions with an incremental flight performance algorithm. A trade-off study is performed using the retracted or faired landing gear's weight increase as a variable. The analysis reveals only small mission performance gains as the aerodynamic improvements are negated by weight penalties. A new workflow for decision-making is presented that allows to estimate if a change in landing gear configuration is beneficial for a small UAV.
Y1  - 2018
U6  - http://dx.doi.org/10.25967/480058
PB  - DGLR
CY  - Bonn
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  - JOUR
A1  - Finger, Felix
A1  - Braun, Carsten
A1  - Bil, Cees
T1  - Impact of electric propulsion technology and mission requirements on the performance of VTOL UAVs
JF  - CEAS Aeronautical Journal
N2  - One of the engineering challenges in aviation is the design of transitioning vertical take-off and landing (VTOL) aircraft. Thrust-borne flight implies a higher mass fraction of the propulsion system, as well as much increased energy consumption in the take-off and landing phases. This mass increase is typically higher for aircraft with a separate lift propulsion system than for aircraft that use the cruise propulsion system to support a dedicated lift system. However, for a cost–benefit trade study, it is necessary to quantify the impact the VTOL requirement and propulsion configuration has on aircraft mass and size. For this reason, sizing studies are conducted. This paper explores the impact of considering a supplemental electric propulsion system for achieving hovering flight. Key variables in this study, apart from the lift system configuration, are the rotor disk loading and hover flight time, as well as the electrical systems technology level for both batteries and motors. Payload and endurance are typically used as the measures of merit for unmanned aircraft that carry electro-optical sensors, and therefore the analysis focuses on these particular parameters.
Y1  - 2018
U6  - http://dx.doi.org/10.1007/s13272-018-0352-x
SN  - 1869-5582 print
SN  - 1869-5590 online
VL  - 10
IS  - 3
SP  - 843
PB  - Springer
ER  - 
TY  - JOUR
A1  - Finger, Felix
T1  - Vergleichende Leistungs- und Nutzenbewertung von VTOL- und CTOL-UAVs
JF  - Luft- und Raumfahrt : informieren, vernetzen, fördern / Hrsg.: Deutsche Gesellschaft für Luft- und Raumfahrt
Y1  - 2017
SN  - 0173-6264
VL  - 38
IS  - 1
SP  - 44
EP  - 47
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  - 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  - Finger, Felix
A1  - Braun, Carsten
A1  - Bil, Cees
T1  - An Initial Sizing Methodology for Hybrid-Electric Light Aircraft
T2  - AIAA AVIATION Forum 2018 Aviation Technology, Integration, and Operations Conference, Atlanta, Georgia, June 25 - 29, 2018
Y1  - 2018
U6  - http://dx.doi.org/10.2514/6.2018-4229
ER  - 
TY  - JOUR
A1  - Finger, Felix
A1  - Bil, Cees
A1  - Braun, Carsten
T1  - Initial Sizing Methodology for Hybrid-Electric General Aviation Aircraft
JF  - Journal of Aircraft
Y1  - 2019
U6  - http://dx.doi.org/10.2514/1.C035428
SN  - 1533-3868
VL  - 57
IS  - 2
SP  - 245
EP  - 255
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  - Rings, René
A1  - Ludowicy, Jonas
A1  - Finger, Felix
A1  - Braun, Carsten
A1  - Bil, Cees
T1  - Sensitivity Analysis of General Aviation Aircraft with Parallel Hybrid-Electric Propulsion Systems
T2  - Asia Pacific International Symposium on Aerospace Technology. APISAT 2019
Y1  - 2019
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  - http://dx.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  - 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  - http://dx.doi.org/10.25967/490026
SP  - 1
EP  - 14
ER  - 
TY  - CHAP
A1  - Finger, Felix
A1  - Götten, Falk
A1  - Braun, Carsten
A1  - Bil, Cees
T1  - Mass, Primary Energy, and Cost - The Impact of Optimization Objectives on the Initial Sizing of Hybrid-Electric General Aviation Aircraft
T2  - Deutscher Luft- und Raumfahrtkongress 2019, DLRK 2019. Darmstadt, Germany
Y1  - 2019
U6  - http://dx.doi.org/10.25967/490012
SP  - 1
EP  - 17
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  - Götten, Falk
A1  - Finger, Felix
A1  - Havermann, Marc
A1  - Braun, Carsten
A1  - Marino, Matthew
A1  - Bil, Cees
T1  - Full Configuration Drag Estimation of Small-to-Medium Range UAVs and its Impact on Initial Sizing Optimization
T2  - Deutscher Luft- und Raumfahrtkongress - DLRK 2020
Y1  - 2020
ER  - 
TY  - JOUR
A1  - Finger, Felix
A1  - Braun, Carsten
A1  - Bil, Cees
T1  - Comparative assessment of parallel-hybrid-electric propulsion systems for four different aircraft
JF  - Journal of Aircraft
N2  - Until electric energy storage systems are ready to allow fully electric aircraft, the combination of combustion engine and electric motor as a hybrid-electric propulsion system seems to be a promising intermediate solution. Consequently, the design space for future aircraft is expanded considerably, as serial hybrid-electric, parallel hybrid-electric, fully electric, and conventional propulsion systems must all be considered. While the best propulsion system depends on a multitude of requirements and considerations, trends can be observed for certain types of aircraft and certain types of missions. This Paper provides insight into some factors that drive a new design toward either conventional or hybrid propulsion systems. General aviation aircraft, regional transport aircraft vertical takeoff and landing air taxis, and unmanned aerial vehicles are chosen as case studies. Typical missions for each class are considered, and the aircraft are analyzed regarding their takeoff mass and primary energy consumption. For these case studies, a high-level approach is chosen, using an initial sizing methodology. Only parallel-hybrid-electric powertrains are taken into account. Aeropropulsive interaction effects are neglected. Results indicate that hybrid-electric propulsion systems should be considered if the propulsion system is sized by short-duration power constraints. However, if the propulsion system is sized by a continuous power requirement, hybrid-electric systems offer hardly any benefit.
Y1  - 2020
U6  - http://dx.doi.org/10.2514/1.C035897
SN  - 1533-3868
VL  - 57
IS  - 5
PB  - AIAA
CY  - Reston, Va.
ER  - 
TY  - CHAP
A1  - Hippe, Jonas
A1  - Finger, Felix
A1  - Götten, Falk
A1  - Braun, Carsten
T1  - Propulsion System Qualification of a 25 kg VTOL-UAV: Hover Performance of Single and Coaxial Rotors and Wind-Tunnel Experiments on Cruise Propellers
T2  - Deutscher Luft- und Raumfahrtkongress - DLRK 2020
Y1  - 2020
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  - http://dx.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  - 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  - http://dx.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  - JOUR
A1  - Götten, Falk
A1  - Finger, Felix
A1  - Havermann, Marc
A1  - Braun, Carsten
A1  - Marino, M.
A1  - Bil, C.
T1  - Full configuration drag estimation of short-to-medium range fixed-wing UAVs and its impact on initial sizing optimization
JF  - CEAS Aeronautical Journal
N2  - The paper presents the derivation of a new equivalent skin friction coefficient for estimating the parasitic drag of short-to-medium range fixed-wing unmanned aircraft. The new coefficient is derived from an aerodynamic analysis of ten different unmanned aircraft used for surveillance, reconnaissance, and search and rescue missions. The aircraft is simulated using a validated unsteady Reynolds-averaged Navier Stokes approach. The UAV’s parasitic drag is significantly influenced by the presence of miscellaneous components like fixed landing gears or electro-optical sensor turrets. These components are responsible for almost half of an unmanned aircraft’s total parasitic drag. The new equivalent skin friction coefficient accounts for these effects and is significantly higher compared to other aircraft categories. It is used to initially size an unmanned aircraft for a typical reconnaissance mission. The improved parasitic drag estimation yields a much heavier unmanned aircraft when compared to the sizing results using available drag data of manned aircraft.
KW  - Parasitic drag
KW  - UAV
KW  - CFD
KW  - Aircraft sizing
Y1  - 2021
U6  - http://dx.doi.org/10.1007/s13272-021-00522-w
SN  - 1869-5590 (Online)
SN  - 1869-5582 (Print)
N1  - Corresponding author: Falk Götten
VL  - 12
SP  - 589
EP  - 603
PB  - Springer
CY  - Berlin
ER  - 
TY  - JOUR
A1  - Finger, Felix
A1  - Götten, Falk
A1  - Braun, Carsten
A1  - Bil, Cees
T1  - Mass, primary energy, and cost: the impact of optimization objectives on the initial sizing of hybrid-electric general aviation aircraft
JF  - CEAS Aeronautical Journal
N2  - For short take-off and landing (STOL) aircraft, a parallel hybrid-electric propulsion system potentially offers superior performance compared to a conventional propulsion system, because the short-take-off power requirement is much higher than the cruise power requirement. This power-matching problem can be solved with a balanced hybrid propulsion system. However, there is a trade-off between wing loading, power loading, the level of hybridization, as well as range and take-off distance. An optimization method can vary design variables in such a way that a minimum of a particular objective is attained. In this paper, a comparison between the optimization results for minimum mass, minimum consumed primary energy, and minimum cost is conducted. A new initial sizing algorithm for general aviation aircraft with hybrid-electric propulsion systems is applied. This initial sizing methodology covers point performance, mission performance analysis, the weight estimation process, and cost estimation. The methodology is applied to the design of a STOL general aviation aircraft, intended for on-demand air mobility operations. The aircraft is sized to carry eight passengers over a distance of 500 km, while able to take off and land from short airstrips. Results indicate that parallel hybrid-electric propulsion systems must be considered for future STOL aircraft.
Y1  - 2020
U6  - http://dx.doi.org/10.1007/s13272-020-00449-8
SN  - 1869-5590
N1  - Corresponding author: Felix Finger
VL  - 2020
IS  - 11
SP  - 713
EP  - 730
PB  - Springer
CY  - Heidelberg
ER  - 
TY  - CHAP
A1  - Finger, Felix
A1  - de Vries, Reynard
A1  - Vos, Roelof
A1  - Braun, Carsten
A1  - Bil, Cees
T1  - A comparison of hybrid-electric aircraft sizing methods
T2  - AIAA Scitech 2020 Forum
Y1  - 2020
U6  - http://dx.doi.org/10.2514/6.2020-1006
N1  - AIAA Scitech 2020 Forum, Driving aerospace solutions for global challenges, Orlando, 06. - 10. January 2020
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  - 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  - Götten, Falk
A1  - Finger, Felix
A1  - Marino, Matthew
A1  - Bil, Cees
A1  - Havermann, Marc
A1  - Braun, Carsten
T1  - A review of guidelines and best practices for subsonic aerodynamic simulations using RANS CFD
T2  - Asia-Pacific International Symposium on Aerospace Technology (APISAT), At Gold Coast, Australia, 04. - 06. Dezember 2019
Y1  - 2019
SN  - 978-1-925627-40-4
ER  - 
TY  - JOUR
A1  - Finger, Felix
A1  - Braun, Carsten
A1  - Bil, Cees
T1  - Impact of Battery Performance on the Initial Sizing of Hybrid-Electric General Aviation Aircraft
JF  - Journal of Aerospace Engineering
N2  - Studies suggest that hybrid-electric aircraft have the potential to generate fewer emissions and be inherently quieter when compared to conventional aircraft. By operating combustion engines together with an electric propulsion system, synergistic benefits can be obtained. However, the performance of hybrid-electric aircraft is still constrained by a battery’s energy density and discharge rate. In this paper, the influence of battery performance on the gross mass for a four-seat general aviation aircraft with a hybrid-electric propulsion system is analyzed. For this design study, a high-level approach is chosen, using an innovative initial sizing methodology to determine the minimum required aircraft mass for a specific set of requirements and constraints. Only the peak-load shaving operational strategy is analyzed. Both parallel- and serial-hybrid propulsion configurations are considered for two different missions. The specific energy of the battery pack is varied from 200 to 1,000 W⋅h/kg, while the discharge time, and thus the normalized discharge rating (C-rating), is varied between 30 min (2C discharge rate) and 2 min (30C discharge rate). With the peak-load shaving operating strategy, it is desirable for hybrid-electric aircraft to use a light, low capacity battery system to boost performance. For this case, the battery’s specific power rating proved to be of much higher importance than for full electric designs, which have high capacity batteries. Discharge ratings of 20C allow a significant take-off mass reduction aircraft. The design point moves to higher wing loadings and higher levels of hybridization if batteries with advanced technology are used.
Y1  - 2020
U6  - http://dx.doi.org/10.1061/(ASCE)AS.1943-5525.0001113
SN  - 1943-5525
VL  - 33
IS  - 3
PB  - ASCE
CY  - Reston, Va.
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  - JOUR
A1  - Finger, Felix
A1  - Götten, Falk
T1  - Neue Ansätze für die Entwicklung von unbemannten Fluggeräten
JF  - Ingenieurspiegel
N2  - Wie sieht das unbemannte Flugzeug von Übermorgen aus? Dieser Frage stellen sich Forscher an der Fachhochschule Aachen. Die weltweit rasant fortschreitende Entwicklung des Marktes für unbemannte Fluggeräte (UAVs - „Unmanned Aerial Vehicles“) bietet großes Potenzial für Wachstum und Wertschöpfung. Unbemannte fliegende Systeme können – für bestimmte Anwendungsgebiete – wesentlich günstiger, kleiner und effizienter ausgelegt werden als bemannte Lösungen. Dabei sind sich viele Unternehmen über das mögliche Potential dieser Technologie noch gar nicht bewusst.
Y1  - 2019
SN  - 1868-5919
N1  - Project: UAV Design
VL  - 2019
IS  - 1
SP  - 67
EP  - 68
ER  - 
TY  - JOUR
A1  - Götten, Falk
A1  - Finger, Felix
T1  - PhoenAIX – Die modulare Transportdrohne
JF  - Ingenieurspiegel
N2  - Die autonome, unbemannte Luftfahrt ist einer der Schlüsselsektoren für die Zukunft der Luftfahrt. In diesem rasant wachsenden Bereich nehmen senkrecht startende und senkrecht landende Flugzeuge (Vertical Take-Off and Landing – VTOL) einen besonderen Platz ein. Ein VTOL-Flugzeug (manchmal auch „Transitionsfluggerät“ genannt) verbindet die Eigenschaft des Helikopters, überall starten und landen zu können, mit den Geschwindigkeits-, Reichweiten und Flugdauervorteilen des Starrflüglers. Grundsätzlich wird die Senkrechtstart- und -landefähigkeit sowohl von zivilen als auch von militärischen Betreibern unbemannter Fluggeräte (UAVs) gewünscht. Trotzdem bietet der Markt nur eine geringe Anzahl von VTOL-UAVs, da qualitativ hochwertige Entwürfe eine ausgesprochene Herausforderung in der Entwicklung darstellen. An der FH Aachen wird deshalb seit über 5 Jahren an der Auslegung und Analyse von solchen unbemannten VTOL Flugzeugen geforscht. Das neuste Projekt ist der Eigenentwurf einer großen, senkrechtstartenden Transportdrohne. Das „PhoenAIX“ getaufte Fluggerät wird von Falk Götten und Felix Finger im Rahmen einer EFRE-Förderung entwickelt.
Y1  - 2020
SN  - 1868-5919
N1  - Project: UAV Design
VL  - 2020
IS  - 1
SP  - 38
EP  - 40
PB  - Public Verlag
CY  - Bingen
ER  -