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    FMI-basierte Simulationskopplung fuer virtuelle Integration und Test eines Hinterkantenklappensystems
    (2021-08)
    Peikert, Matthias
    ;
    Thielecke, Frank
    In diesem Paper wird die Eignung des Functional Mock-Up Interface (FMI) zur virtuellen Integration und Testen von Flugzeugsystemmodellen untersucht. Als Beispielanwendung wird ein Hochauftriebssystem betrachtet. Dabei soll das fl exible Mehrkörpermodell einer Hinterkantenklappe mit einem Antriebs- und Transmissionsmo- dell per FMI gekoppelt werden. Neben der prinzipiellen Implementierung der Kopplung steht eine Bewertung des kopplungsinduzierten Simulationsfehlers im Fokus der Untersuchung.
    Publicationtype: Conference Paper
      79
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    Comparison of electro-hydraulic and electro-mechanic landing gear actuation for light VTOL aircraft
    (2021-09)
    Springmann, Raphael
    ;
    Thielecke, Frank
    In this paper, a landing gear actuation system for a light VTOL aircraft is predesigned aiming for minimal power consumption and low weight. Electro-hydraulic and electro-mechanic system architectures are taken into account.
    Publicationtype: Conference Presentation
      122
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    Fuel-efficient flight control design for a hypersonic airliner
    (Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V. (DGLR), 2021-08)
    Bodmer, Daniel
    ;
    Shah, Rhea Deven
    ;
    Linke, Florian
    ;
    Gollnick, Volker
    The determination of realistic flight mission characteristics, such as fuel consumption and flight time, requires fuel-optimal flight trajectories where the vehicles total trip fuel converges to a minimum. Within the Stratospheric Flying Opportunities for High-Speed Propulsion Concepts research project, one of the main challenging factors is the design of artificial flight controllers for maintaining 4D fuel-optimal trajectories for the STRATOFLY MR3 vehicle. In this paper, we propose a continuous climb cruise (CCC) flight controller as well as a zoom dive (ZD) flight controller which are derived using Feedback Linearization and embedded in a MATLAB-based trajectory simulation program. This incorporates the establishment of a proper control design model, an aircraft state estimator and the limitation of the plants control inputs to ensure a bounded fast-time, forward integration of all aircraft state variables based on a 3 degrees of freedom point-mass model. Simulation results are presented showing that the CCC controller is primarily used in the hypersonic cruise phase - covering the main flight segment of MR3 - and that the ZD controller is used in the transonic region (while the vehicle reaches Mach 1), both ensuring a total decay of 2.98 % in the vehicles fuel consumption for a reference flight mission from Brussels to Sydney.
    Publicationtype: Conference Paper
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