A convertible aircraft (1, 1') with an airframe (2) defining a first longitudinal axis (Y) is described; a pair of half-wings (3); a first, a second, a third, a fourth, a fifth and a sixth rotor (20a, 20b, 21a, 21b, 22a, 22b) rotatable about respective first, second, third, fourth, fifth and sixth axis (B, C, D, E, F, G), and operable independently of each other so as to generate respectively a first, a second, a third, a fourth, a fifth and a sixth thrust value (T1, T2, T3, T4, T5, T6) independent of each other; said fifth and sixth rotor (22a, 22b) being carried by respective said half-wings (3) and inclinable with respect to said airframe (2); the aircraft (1, 1') being switchable between a first hovering flight configuration wherein the sixth and seventh axis (F, G) are arranged orthogonal to the first axis (Y); and a second forward flight configuration wherein the sixth and seventh axis (F, G) are arranged parallel to or inclined with respect to the first axis (Y); the aircraft (1, 1') comprises first supports (32a, 32b) adapted to support the fifth and sixth rotor (22a, 22b) with respect to the respective half-wings (3); the first supports (32a, 32b) being arranged spaced apart from respective free ends (15) of respective half-wings (3) according to an extension direction of respective half-wings (3).
CONVERTIBLE AIRCRAFT CAPABLE OF HOVERING
14.12.2023
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |