VTOL aircraft with a thrust-to-weight ratio smaller than 0.1, during vertical take-off/landing, obtains an another lift, besides a lift generated by low-temp bypass duct (15) directing the low-temp air (18) from the turbofan engine (3) to flow, through its outlet (19) in form of low-temp planar jet (20), over the upper surface of the wing and in the direction of the wingspan, by high-temp bypass duct (15) directing the high-temp air (18) from the turbofan engine (3) to flow, through its outlet (12) in form of high-temp planar jet (13), above the low-temp planar jet (20) in the direction of the wingspan and enables the ailerons (1, 2) to control the balances of the aircraft more efficiently.


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    Titel :

    VTOL AIRCRAFT WITH A THRUST-TO-WEIGHT RATIO SMALLER THAN 0.1


    Weitere Titelangaben:

    SENKRECHTSTARTERFLUGZEUG MIT EINEM SCHUBGEWICHTSVERHÄLTNIS KLEINER ALS 0,1
    AÉRONEF ADAV AYANT UN RAPPORT POUSSÉE-MASSE INFÉRIEUR À 0,1


    Beteiligte:
    CHEN LI JING (Autor:in)

    Erscheinungsdatum :

    26.09.2018


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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