The operational use of tilt-wing aircraft is becoming increasingly important in many areas of civil unmanned aviation. Combining the advantages of vertical take-off and landing with the efficiency of fixed-wing flight, tilt-wing aircraft offer high performance and great flexibility in operational scenarios. Flight missions such as support for rescue operations and aerial camera assistance place high demands on safety, efficiency and highly dynamic operation of unmanned aerial vehicles, as well as the legal framework for the operation of unmanned aerial systems. Within this thesis, the performance of tilt-wing aircraft is defined as a high level of dynamics that utilizes the entire flight envelope while maintaining a high level of efficiency. In this thesis, a performance-optimized flight state control system is developed and evaluated to enable safe, highly dynamic operation in the entire flight envelope of a tilt-wing aircraft. Highly dynamic flight state changes are essential for tilt-wing aircraft in order to achieve complex flight paths while quickly transitioning to more efficient flight states. The flight control system must therefore provide high performance across the entire flight envelope in order to fulfill the flight mission efficiently. In addition, challenging areas at the limits of the flight envelope are developed and rapid flight state changes throughout the entire flight envelope are targeted. In order to meet the high performance requirements, a new approach to the design of flight state control for tilt-wing aircraft is being developed. In addition to pure stabilization, performance evaluation criteria are formulated to achieve safe, highly dynamic operation from hover to fast forward flight by determining optimal paths for trim controls. In order to achieve rapid changes in flight state, the allocation of control device commands is optimized across the entire flight envelope. The flight state controller developed with the design method, utilizing an LQR attitude control, is validated in the entire flight envelope using the tilt-wing aircraft NEO, especially with respect to highly dynamic flight state changes. A non-linear simulation and final flight tests are used to demonstrate the efficiency of the designed flight state controller and the optimized performance of the tilt-wing aircraft.


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    Titel :

    Performanz-optimierte Flugzustandsregelung für ein hochdynamisches Kippflügel-Fluggerät


    Weitere Titelangaben:

    Performance-optimized flight state controller for highly dynamic tilt-wing aircraft


    Beteiligte:
    Osterloh, Patrick (Autor:in) / Moormann, Dieter (Akademische:r Betreuer:in) / Behr, Marek (Akademische:r Betreuer:in)

    Erscheinungsdatum :

    01.01.2024


    Format / Umfang :

    1 Online-Ressource : Illustrationen pages


    Anmerkungen:

    Dissertation, Rheinisch-Westfälische Technische Hochschule Aachen, 2024; Aachen : RWTH Aachen University 1 Online-Ressource : Illustrationen (2024). doi:10.18154/RWTH-2024-08027 = Dissertation, Rheinisch-Westfälische Technische Hochschule Aachen, 2024



    Medientyp :

    Sonstige


    Format :

    Elektronische Ressource


    Sprache :

    Deutsch


    Schlagwörter :



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