- ZAGIL is a light UAV flies with 0.6 Mach number and maximum working altitude of 8 km. It has a wingspan of 2.38 m. The original design of the UAV wing has structural problem from an aeroelasticity point of view. This problem represented in a highly stressed semi-monocoque structure of the wing that contains the skin, ribs, spar and trailing edge at operating condition Mach number of 0.6 and angle of attack 10 degrees. The paper studied this phenomenon which considered as a main structural problem in the original wing of ZAGIL UAV by enhancing computational software, theoretical approach and experimental test. The redesign solution for the wing is approved to satisfy the working operating condition for the UAV. In wing redesign, the skin is compacted with the leading edge, trailing edge and spar using the extrusion technology to manufacture the wing without rips. The CFD simulation is used to compare the aerodynamic results, while an experimental test result is used to validate the structural result which both obtained by finite element modeling and post processing FEMAP software. The results represent that the redesigned wing structure is stiffer than the original wing by 51% and less stressed by 19% in the wing root attachment zone.


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    Titel :

    Redesign of Light Aircraft (Zagil) Wing


    Beteiligte:
    Omer, Mohamed (Autor:in) / Abu Darag, Sakhr (Autor:in)

    Erscheinungsdatum :

    04.11.2021


    Anmerkungen:

    Journal of Engineering and Computer Science (JECS); Vol 22, No 2 (2021); 62-71 ; 1858-6791 ; 1858-6783


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



    Klassifikation :

    DDC:    621




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