| 摘要 |
The invention concerns a convertible aircraft comprising a fuselage (F), a pair of wings (A1, A2) disposed to either side of the fuselage (F), at least one ducted rotor (1) installed in a horizontal position at one of the ends of the fuselage (F), and first and second nacelles (N1, N2) disposed respectively at the end of each wing (A1, A2), each comprising a ducted rotor (R1, R2), and tiltably mounted relative to the fuselage (F), characterised in that they comprise at least first and second movable flaps (V1, V2), disposed respectively at the outlet of the ducted rotor (R1) of the first nacelle (N1) and at the outlet of the ducted rotor (R2) of the second nacelle (N2). The aircraft according to the invention thus represents an advantageous solution for all applications involving helicopters and aeroplanes, and in particular civil security, rescue, and public or private transport missions. |
