초록 ▼

There is described a convertiplane comprising: a pair of semi-wings; a first rotor comprising a shaft which may rotate about first axis and tilt about a second axis together with first axis with respect to semi-wings between a helicopter mode and an aeroplane mode; first axis being transversal to a

There is described a convertiplane comprising: a pair of semi-wings; a first rotor comprising a shaft which may rotate about first axis and tilt about a second axis together with first axis with respect to semi-wings between a helicopter mode and an aeroplane mode; first axis being transversal to a longitudinal direction of convertiplane in helicopter mode and being substantially parallel to longitudinal direction in aeroplane mode; convertiplane also comprises an electrical power storage device; and an electrical machine which comprises, in turn: a stator electrically connected to storage device; and a second rotor operatively connected to a shaft of first rotor; electrical machine acts as an electric motor for driving in rotation said first rotor by using the electrical power stored in storage device; or as an electrical power generator for re-charging storage device by causing the rotation second rotor under the action of a wind current.

대표청구항 ▼

1. A convertiplane (1) comprising: a pair of semi-wings (3);at least one first rotor (4) comprising a shaft (6) which may rotate about relative first axis (B) and tilt about a second axis (C) together with said first axis (B) with respect to said semi-wings (3) between a helicopter mode and an aerop

1. A convertiplane (1) comprising: a pair of semi-wings (3);at least one first rotor (4) comprising a shaft (6) which may rotate about relative first axis (B) and tilt about a second axis (C) together with said first axis (B) with respect to said semi-wings (3) between a helicopter mode and an aeroplane mode;said first axis (B) being, in use, transversal to a longitudinal direction (A) of said convertiplane (1) in said helicopter mode and being, in use, substantially parallel to said longitudinal direction (A) in said aeroplane mode;characterized by comprising:at least one first actuator (52), which is adapted to control the tilting of said first rotor (4) about relative second axis (C);a flight control system (49) for controlling said actuator (52);an electrical power storage device (70; 81, 82); andat least one electrical machine (71);said actuator (52) comprising, in turn:a fixed part (53);a ram (54), which may slide parallel to said longitudinal direction (A) relative to said fixed part (53);a rod (55) having a first end (56) hinged to said ram (54) about an axis parallel to said second axis (C), and a second end (58) which integrally tilts with said rotor (4);a control unit (51), which controls the movement of said ram (54) parallel to said longitudinal direction (A) and is controlled by control system (49) on the basis of a plurality of flight and mission parameters;said electrical machine (71) comprising, in turn:a stator (72) which is electrically connected to said storage device (70; 81, 82); anda second rotor (73) which is operatively connected to a shaft (6) of said first rotor (4);said electrical machine (71) being operable as:an electric motor for driving in rotation said first rotor (4) by using the electrical power stored in said storage device (70; 81, 82); oras an electrical power generator for re-charging said storage device (70; 81, 82) by causing the rotation of said first rotor (4) under the action of a wind current, when said convertiplane (1) is on ground in said aeroplane mode and said storage device (70; 81, 82) needs to be re-charged;said first rotor (4) being tiltable about said second axis (C) in a direction facing the wind current, when said convertiplane (1) is on ground in said aeroplane mode and said storage device (70; 81, 82) needs to be re-charged;said wind-current driving in rotation said shaft (6) of said first rotor (4), which, in turn, causes the rotation of said second rotor (73) of said electrical machine (71) relative to said stator (72), when said convertiplane (1) is on ground in said aeroplane mode;said flight control system (49) comprising detecting means for detecting said direction facing the wind and controlling said control unit (51) of said actuator (52), so as to tilt said first rotor (4) in said direction facing the wind, when said convertiplane (1) is on ground in said aeroplane mode. 2. Convertiplane according to claim 1, characterized in that said shaft (6) and said first rotor (4) are directly connected to each other. 3. Convertiplane according to claim 1, characterized in that said electrical machine (71) defines, when operated as electrical power generator, braking means to slow down said rotational of motion of first rotor (4) while charging said storage device (70). 4. Convertiplane according to claim 1, characterized in that said electrical machine (71) is an axial flux electrical machine which generates, in use, a magnetic flux with a main component parallel to said first axis (B). 5. Convertiplane according to claim 1, characterized in that said electrical machine (71) is a brushless electric machine. 6. Convertiplane according to claim 1, characterized in that said electrical machine (71) comprises: at least one permanent magnet (76) integrally movable with said second rotor (73); andat least one coil (75) fitted to said stator (72), magnetically coupled with said permanent magnet (76) and which may be electrically fed by said storage device (70; 81, 82). 7. Convertiplane according to claim 6, characterized by comprising two said electrical machines (71) comprising relative first rotors (4) which are directly connected to said shaft (6) of said first rotor (4). 8. Convertiplane according to claim 1, characterized by comprising: a common core comprising said first rotor (4) and said electric machine (71); anda module comprising said storage device (70; 81, 82) which may be selectively connected to said common core;said storage device (70; 81, 82) comprising:either an electrical battery (81); ora hybrid battery (82) and an internal combustion engine (83) operatively connected with said hybrid battery (82). 9. Convertiplane according to claim 8, characterized in that said internal combustion engine (83) is a Diesel engine. 10. Convertiplane according to claim 1, characterized by comprising: a plurality of blades (27) articulated relative to said shaft (6); and/orat least one elevon (40) movable relative to said semi-wings (3); and/orat least one landing gear (9) which may extended or withdrawn; and/orat least one second actuator (100) for varying the position of a relative said blade (27) of said first rotor (4) relative to said shaft (6); and/orat least one third actuator for controlling the position of said elevon (40) relative to said semi-wings (3); and/orat least one further fourth actuator for controlling the extension/withdrawal of said landing gear (9);at least one of said first, second, third and fourth actuator (100, 52) being an electro-mechanical actuator. 11. A method of operating a convertiplane (1); said convertiplane (1) comprising: a pair of semi-wings (3);at least one first rotor (4) which may rotate about relative first axis (B) and tilt about a second axis (C) together with said first axis (B) with respect to said semi-wings (3) between a helicopter mode and an aeroplane mode;said first axis (B) being, in use, transversal to a longitudinal direction (A) of said convertiplane (1) in said helicopter mode and being, in use, substantially parallel to said longitudinal direction (A) in said aeroplane mode;said method being characterized by comprising the steps of:operating an electrical machine (71) as an electric motor for driving in rotation said first rotor (4) by using the electrical power stored in an electrical power storage device (70; 81, 82); andoperating said electrical machine (71) as an electric power generator for re-charging said storage device (70; 81, 82);said step of operating said electrical machine (71) as an electric power generator comprising the step of using wind energy for driving in rotation said first rotor (4) when said convertiplane (1) is on ground in said aeroplane mode;said convertiplane (1) comprising:at least one actuator (52), which is adapted to control the tilting of said first rotor (4) about relative second axis (C);a flight control system (49) for controlling said actuator (52);said actuator (52) comprising, in turn:a fixed part (53);a ram (54), which may slide parallel to said longitudinal direction (A) relative to said fixed part (53);a rod (55) having a first end (56) hinged to said ram (54) about an axis parallel to said second axis (C), and a second end (58) which integrally tilts with said rotor (4);a control unit (51), which controls the movement of said ram (54) parallel to said longitudinal direction (A) and is controlled by control systempluralityof flight and mission parameters;said electrical power storage device (70; 81, 82); andsaid at least one electrical machine (71);said electrical machine (71) comprising, in turn:a stator (72) which is electrically connected to said storage device (70; 81, 82); anda second rotor (73) which is operatively connected to said first rotor (4);characterized by comprising the step of tilting said first rotor (4) of a given angle about said second axis (C) before said step of operating said electrical machine (71) as an electric motor, when said convertiplane (1) is on ground in said aeroplane mode and said storage device (70; 81, 82) needs to be re-charged;said given angle being associated to a main direction of the wind-current;said wind-current driving in rotation said shaft (6) of said first rotor (4), which, in turn, causes the rotation of said second rotor (73) of said electrical machine (71) relative to said stator (72), when said convertiplane (1) is on ground in said aeroplane mode;said flight control system (49) detecting said direction facing said wind current and controlling said control unit (51) of said actuator (52) so as to tilt said first rotor (4) in said direction facing said wind current, when said convertiplane (1) is on ground in said aeroplane mode. 12. The method of claim 11, characterized in that said step of operating said electrical machine (71) as an electric power generator comprises the step of braking said first rotor (4).