This paper presents the pitching moment stability analysis and adjustment for tilt-wing unmanned aerial vehicle (UAV) in hovering flight and vertical take-off and landing (VTOL). The tilt-wing UAVs combine the features of fixed-wing UAVs with VTOL capabilities by tilting the wing and rotor system for the transition between flight modes. Due to its hybrid configuration, the altitude control study, position and attitude, poses a major problem during the entire flight for a given mission. Namely, in the first flight phase the pitching moment could present instabilities with different disturbances, such as wind, that are difficult to compensate. In this paper this problem is analyzed and possible solutions for the stabilization are presented and evaluated in a test bench. These solutions were implemented in new test prototypes demonstrating satisfactory results in outdoor flight tests.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Pitching moment analysis and adjustment for tilt-wing UAV in VTOL mode


    Beteiligte:


    Erscheinungsdatum :

    01.06.2019


    Format / Umfang :

    614740 byte





    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



    ENHANCED NET PITCHING MOMENT MULTI-WING VTOL COMPACT PERSONAL AIRCRAFT

    GRAHAM BRENDAN | Europäisches Patentamt | 2018

    Freier Zugriff

    Enhanced net pitching moment multi-wing VTOL compact personal aircraft

    GRAHAM BRENDAN | Europäisches Patentamt | 2019

    Freier Zugriff

    Tilt-wing VTOL aircraft

    McCormick, Jr., B.W. / Mallen, J. | Engineering Index Backfile | 1957


    Wing pitching moment coefficient

    Morse, W.L. | Engineering Index Backfile | 1945


    WING TILT SCHEDULING IN TANDEM-WING VTOL CONFIGURATIONS

    Grzedzinski, K. / Stephan, V. / Zolotas, A. | TIBKAT | 2021