An aircraft (1) comprising a fuselage (2, 2', 2") with a nose (4) and a tail (5) arranged on opposite parts to each other along a first longitudinal axis (Y) is described; a pair of half-wings (3) arranged on respective mutually opposite sides of the fuselage (2, 2', 2'); a first and a second rotor (22a, 22b) carried by respective half-wings (3), respectively rotatable around a second and third axis (F, G) inclinable with respect to said fuselage (2, 2', 2"), and independently operable from each other; the aircraft (1) is switchable between a first hovering flight or take-off/landing configuration wherein the fourth and fifth axis (F, G) are arranged orthogonal to said first axis (Y); and a second forward flight configuration wherein the fourth and fifth axis (F, G) are arranged parallel or inclined with respect to said first axis (Y); the aircraft (1) further comprising a tail portion (6) comprising a first aerodynamic surface (8), and a third and a fourth rotor (21a, 21b) rotatable around a fixed fourth and a fifth axis (D, E); and support means (31a, 31b) of the third and fourth rotor (21a, 21b) connected to a corresponding said half-wing (3) and to a corresponding said drift (52). (Figure 9)


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    Title :

    CONVERTIBLE AIRCRAFT CAPABLE OF HOVERING


    Additional title:

    UMWANDELBARES SCHWEBEFLUGFÄHIGES LUFTFAHRZEUG
    AÉRONEF CONVERTIBLE CAPABLE DE VOL STATIONNAIRE


    Contributors:

    Publication date :

    2023-11-22


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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