| CPC B64C 27/28 (2013.01) [B64C 29/0033 (2013.01)] | 9 Claims |
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1. A convertible aircraft (1, 1′) comprising:
an airframe (2) defining a first longitudinal axis (Y) of said aircraft (1, 1′);
a pair of half-wings (3) arranged on respective mutually opposite sides of sidewalls (62) of said airframe (2) and generating, in use, a first lift or downforce value;
a first and a second rotor (20a, 20b) which are rotatable respectively about a second and a third axis (B, C) and fixed with respect to said airframe (2), and operable independently of each other so as to generate respectively a first and a second thrust value (T1, T2) independent of each other;
a third and a fourth rotor (21a, 21b) which are rotatable, respectively, about a fourth and fifth axis (D, E) and fixed with respect to said airframe (2), and operable independently of each other so as to generate, respectively, a third and a fourth thrust value (T3, T4) independent of each other;
said second and third axis (B, C) being arranged respectively on a first and a second sidewall (62) that are opposite to each other of said airframe (2) symmetrically with respect to said first axis (Y):
said fourth and fifth axis (D, E) being arranged on respective sides of said first and second sidewall (62) of said airframe (2) symmetrically with respect to said first axis (Y);
said aircraft (1, 1′) further comprising:
a fifth and a sixth rotor (22a, 22b) carried by respective said half-wings (3), which are rotatable respectively about a sixth and seventh axis (F, G) inclinable with respect to said airframe (2), and operable independently of each other so as to generate respectively a fifth and a sixth thrust value (T5, T6) independent of each other;
said sixth and seventh axis (F, G) being arranged on respective sides of said first and second sidewall (62) of said airframe (2) symmetrically with respect to said first axis (Y);
said aircraft (1, 1′) being switchable between:
a first hovering or take-off/landing flight configuration wherein said sixth and seventh axis (F, G) are arranged orthogonal to said first axis (Y); and
a second forward flight configuration wherein said sixth and seventh axis (F, G) are arranged parallel to or inclined with respect to said first axis (Y);
first supports (32a, 32b) adapted to support said fifth and sixth rotor (22a, 22b) with respect to the relative half-wings (3); said first supports (32a, 32b) being arranged at a distance from respective free ends (15) of respective said half-wings (3) according to an extension direction of said half-wings (3);
wherein said fifth and sixth rotors (22a, 22b) are interposed between said first and second rotor (20a, 20b) and said third and fourth rotor (21a, 21b) along said first axis (Y);
said first, third and fifth axis (B, D, F) being aligned with each other along said first axis (Y) when said aircraft (1, 1′) is arranged in said first configuration;
said second, fourth and sixth axis (C, E, G) being aligned with each other along said first axis (Y) when said aircraft (1, 1′) is arranged in said first configuration;
said second, third, fourth and fifth axis (B, C, D, E) being parallel to each other;
a fin (7) which is arranged at a tail (6) of said airframe (2); and
second supports (31a, 31b) which are provided to support said third and fourth rotor (21a, 21b) with respect to said airframe (2); said second supports (31a, 31b) being arranged on respective mutually opposite sidewalls (62) of said fin (7) and posteriorly to respective said half-wings (3), with reference to a normal operating position of said aircraft (1, 1′) arranged, in use, in said second configuration;
wherein said fin (7) extends from both the upper and lower sides of said airframe (2); and/or
wherein said fin (7) carries a first carriage (46);
wherein said fin (7) comprises a pair of first aerodynamic surfaces (8, 8′) which are fixed and project cantilevered from respective mutually opposite sides (62) of said fin (7); said first aerodynamic surfaces (8, 8′) being adapted to generate, in use, a second lift/downforce value.
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