| CPC B64U 30/10 (2023.01) [B64C 29/0033 (2013.01); B64D 27/33 (2024.01); B64D 31/09 (2024.01); B64U 10/16 (2023.01); B64U 10/25 (2023.01); B64U 30/20 (2023.01); B64U 50/13 (2023.01); B64U 50/19 (2023.01)] | 6 Claims |
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1. Series of aircrafts (1, 1′) that can be converted and configured in respective mutually distinct architectures based on the operational needs of the aircrafts (1, 1′); each said aircraft (1, 1′) of said series comprising:
a core (100) that is common to all said architectures;
said core (100) comprising:
an airframe (2) defining a first longitudinal axis (Y) of said aircraft (1, 1′);
a first and a second rotor (20a, 20b) which are rotatable, respectively, about a second and third axis (B, C) which is fixed with respect to said airframe (2), and which are 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) which is fixed with respect to said airframe (2), and which are 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, third, fourth and fifth axis (B, C, D, E) being parallel to each other;
said second and third axis (B, C) being arranged respectively on respective sides of a first and a second sidewall (62) that are opposite to each other of said airframe (2) and symmetrically with respect to said first axis (Y);
said fourth and fifth axis (D, E) being arranged respectively on respective said sides of said first and second sidewall (62) of said airframe (2) and symmetrically with respect to said first axis (Y);
each said aircraft (1, 1′) of said series further comprising:
a fifth and a sixth rotor (22a, 22b) carried by respective half-wings (3), which are rotatable respectively about a sixth and a seventh axis (F, G), 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 respectively on respective said sides of said first and second sidewall (62) of said airframe (2) symmetrically with respect to said first axis (Y);
said sixth and seventh axis (F, G) being inclinable with respect to said airframe (2);
each said aircraft (1, 1′) of said series 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);
said core (100) of each aircraft (1, 1′) of said series further comprising:
a rechargeable electric power source (81);
a plurality of electric motors (72a, 72b, 73a, 73b, 74a, 74b) and operatively connected to said first, second, third, fourth, fifth and sixth rotor (20a, 20b, 21a, 21b, 22a, 22b);
each said aircraft (1, 1′) of said series comprising a respective module (120, 130) associated with a respective said architecture and interfaced with said core (100);
characterized in that said module (120, 130) defines a hybrid propulsion system (74);
said module (120, 130) comprising:
a control unit (71);
a first heat engine (80) configured to generate a first mechanical power value;
a second heat engine (90) configured to generate a second mechanical power value greater than said first mechanical power value;
first electric generators (82) configured to generate a first electric power value, which are electrically selectively connected to said electric motors (72a, 72b, 73a, 73b, 74a, 74b) and operable by said first heat engine (80); and
second electric generators (91) configured to generate a second electric power value greater than said first value and electrically selectively connected with said electric motors (72a, 72b, 73a, 73b, 74a, 74b) and operable by said second heat engine (80);
said control unit (71) being programmed to:
electrically connect said second electric generators (91) and said rechargeable electric power source (81) to said electric motors (72a, 72b, 73a, 73b, 74a, 74b), when said aircraft (1, 1′) is arranged in said first configuration for a first time interval; and
electrically connect said second and first electric generators (91, 82) and said rechargeable electric power source (81) to said electric motors (72a, 72b, 73a, 73b, 74a, 74b), when said aircraft (1, 1′) is arranged in said first configuration for a second time interval greater than said first time interval;
said control unit (71) being programmed to connect said first engine (80) alone to said electric generators (82) and/or to recharge said rechargeable electric power source (81), when said aircraft (1, 1′) is arranged in a second configuration for a second time interval greater than said first time interval;
said control unit (71) being programmed to electrically connect said rechargeable electric power source (81) to said electric motors (72a, 72b, 73a, 73b, 74a, 74b) in case of failure of one of said first and second heat engine (80, 90).
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