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1. 发明申请

WO2021124211A8 CONVERTIPLANE AND ASSOCIATED FOLDING METHOD 审中-公开
公开(公告)号：WO2021124211A8
公开(公告)日：2021-06-24
申请号：PCT/IB2020/062124
申请日：2020-12-17
申请人： LEONARDO S.P.A.
发明人： BIANCO MENGOTTI, Riccardo , PIZZAGALLI, Matteo , CASSINELLI, Carlo , BRUGHERA, Paolo , SAMPUGNARO, Luca
IPC分类号： B64C27/28 , B64C3/56 , B64C29/00 , B64C29/0033
摘要： A method is described for the folding of a convertiplane (1) with a fuselage (2) having a first axis (A), a pair of wings (3) and a pair of rotors (5) arranged on respective mutually opposite sides of the respective wings (3); each rotor (5) comprises a mast (9) rotatable about a second axis (B) and a plurality of blades (8a, 8b); each wing (3) comprises a first portion (20) fixed with respect to the fuselage (2); a second tip portion (21) opposite to the first portion (20); and a third intermediate portion (22), which is interposed between the associated first portion (20) and second tip portion (21); the mast (9) of each rotor (5) is integrally tiltable with the second axis (B) and associated second tip portion (21) about a third axis (E) transversal to the second axis (B) and the fuselage (2) so as to set said convertiplane (1) between a helicopter configuration and an aeroplane configuration; the method comprises the steps i) of arranging the convertiplane (1) in the helicopter configuration and ii) rotating a pair of assemblies (23) of respective wings (3) with respect to the fuselage (2) and the associated first portion (20) about respective fifth axes (I), so as to arrange the convertiplane (1) in a stowage configuration. A convertiplane (1) is also disclosed.

2. 发明申请

WO2021124207A1 CONVERTIPLANE 审中-公开
公开(公告)号：WO2021124207A1
公开(公告)日：2021-06-24
申请号：PCT/IB2020/062120
申请日：2020-12-17
申请人： LEONARDO S.P.A.
发明人： BIANCO MENGOTTI, Riccardo , CASSINELLI, Carlo , SCANDROGLIO, Alessandro , BAVETTA, Andrea , BRUGHERA, Paolo , SAMPUGNARO, Luca
IPC分类号： B64C27/28 , B64C39/12
摘要： A convertiplane (1, 1', 1 '') is described that comprises a fuselage (2), having a first longitudinal axis (A), with a nose (12) and a tail portion (13); a pair of wings (3) arranged on respective opposite sides of said fuselage (2), carrying respective rotors (5); a pair of engines (4) operatively connected to respective said rotors (5); at least one first lifting surface (19, 16) arranged on said tail portion (13); and a pair of canards (14) arranged on said nose (12) of said fuselage (2) and defining respective second lifting surfaces adapted to generate a third 11ft/negative lift value; each rotor (5) comprising a mast (9) rotatable about a second axis (B) and about an relative third axis (E) transversal to said second axis (B) and with respect to the fuselage (2), so as to set said convertiplane (1, 1', 1'') between a helicopter configuration and an aeroplane configuration; each second axis (B), in use, being transversal to the first axis (A) of said convertiplane (1, 1', 1'') in said helicopter configuration and being parallel to said first axis (A) in said aeroplane configuration.

3. 发明申请

WO2021186411A1 HELICOPTER, HELICOPTER KIT AND ASSOCIATED RECONFIGURATION METHOD 审中-公开
公开(公告)号：WO2021186411A1
公开(公告)日：2021-09-23
申请号：PCT/IB2021/052324
申请日：2021-03-19
申请人： LEONARDO S.P.A.
发明人： MELONE, Stefano , CAMPANARDI, Gabriele , MEDICI, Luca , SCANDROGLIO, Alessandro , BIANCO MENGOTTI, Riccardo
IPC分类号： B64C5/02 , B64C27/04 , B64C27/82 , B64C39/06 , B64C3/14
摘要： A helicopter (1) is described comprising a fuselage (2) elongated along a first axis (X) and extending between a nose (6) and a tail boom (7); a tailplane (9) with a pair of first aerodynamic surfaces (11) elongated along a second axis (Y); the first and second axis (X, Y) define a first plane (Q); the helicopter (1) comprises a pair of elements (20) transversal to the first aerodynamic surfaces (11); and a pair of second aerodynamic surfaces (21) generating respective second aerodynamic forces, connected to first elements (20), and facing and spaced from respective first aerodynamic surfaces (11); each second aerodynamic surface (21) comprises one first root end (80) connected to the respective said element (20), a second free end (81) spaced from said tail boom (7), a first leading edge (55), a first trailing edge (56) opposite to said first leading edge (55), a first chord (C1) at said first root end (80) and a second chord (C2) at said second free end (81) parallel to said first axis (X); the first and the second chord (C1, C2) define a second plane (R) tilted with respect to said first plane (Q).

4. 发明申请

WO2021124211A1 CONVERTIPLANE AND ASSOCIATED FOLDING METHOD 审中-公开
公开(公告)号：WO2021124211A1
公开(公告)日：2021-06-24
申请号：PCT/IB2020/062124
申请日：2020-12-17
申请人： LEONARDO S.P.A.
发明人： BIANCO MENGOTTI, Riccardo , PIZZAGALLI, Matteo , CASSINELLI, Carlo , BRUGHERA, Paolo , SAMPUGNARO, Luca
IPC分类号： B64C27/28 , B64C3/56 , B64C29/00 , B64C29/0033
摘要： A method is described for the folding of a convertiplane (1) with a fuselage (2) having a first axis (A), a pair of wings (3) and a pair of rotors (5) arranged on respective mutually opposite sides of the respective wings (3); each rotor (5) comprises a mast (9) rotatable about a second axis (B) and a plurality of blades (8a, 8b); each wing (3) comprises a first portion (20) fixed with respect to the fuselage (2); a second tip portion (21) opposite to the first portion (20); and a third intermediate portion (22), which is interposed between the associated first portion (20) and second tip portion (21); the mast (9) of each rotor (5) is integrally tillable with the second axis (B) and associated second tip portion (21) about a third axis (E) transversal to the second axis (B) and the fuselage (2) so as to set said convertiplane (1) between a helicopter configuration and an aeroplane configuration; the method comprises the steps i) of arranging the convertiplane (1) in the helicopter configuration and ii) rotating a pair of assemblies (23) of respective wings (3) with respect to the fuselage (2) and the associated first portion (20) about respective fifth axes (I), so as to arrange the convertiplane (1) in a stowage configuration. A convertiplane (1) is also disclosed.

5. 发明申请

WO2022263949A1 SERIES OF CONVERTIBLE AIRCRAFT CAPABLE OF HOVERING AND METHOD FOR CONFIGURING A CONVERTIBLE AIRCRAFT CAPABLE OF HOVERING 审中-公开
公开(公告)号：WO2022263949A1
公开(公告)日：2022-12-22
申请号：PCT/IB2022/054836
申请日：2022-05-24
申请人： LEONARDO S.P.A
发明人： BIANCO MENGOTTI, Riccardo
IPC分类号： B64C29/00 , B64C3/56 , B64C39/12
摘要： A series of convertible aircraft (1, 1') with a core (100) with an airframe (2) defining a first axis (Y) is described; a first, a second, a third, a fourth, a fifth and a sixth rotor (20a, 20b, 21a, 21b, 22a, 22b) which are 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 (Tl, T2, T3, T4, T5, T6) independent of each other; the core (100) comprises first and second portions (11, 17) of respective half-wings (3) and aerodynamic surfaces (9) and each module (110, 120, 130, 140) comprises third and fourth portions (12, 18) of respective half-wings (3) and aerodynamic surfaces (9).

6. 发明申请

WO2022263948A1 SERIES OF CONVERTIBLE AIRCRAFTS CAPABLE OF HOVERING AND METHOD FOR CONFIGURING A CONVERTIBLE AIRCRAFT CAPABLE OF HOVERING 审中-公开
公开(公告)号：WO2022263948A1
公开(公告)日：2022-12-22
申请号：PCT/IB2022/054832
申请日：2022-05-24
申请人： LEONARDO S.P.A
发明人： BIANCO MENGOTTI, Riccardo
IPC分类号： B64C29/00 , B64C39/02 , B64C39/08 , B64C39/12
摘要： A series of convertible aircrafts (1, 1') with a core (100) with an airframe (2) defining a first axis (Y) is described; a first, a second, a third, a fourth, a fifth and a sixth rotor (20a, 20b, 21a, 21b, 22a, 22b) which are 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; the core (100) comprises an electric power source (81) and electric motors (72a, 72b, 73a, 73b, 74a, 74b) which are connected to said first, second, third, fourth, fifth and sixth rotor (20a, 20b, 21a, 21b, 22a, 22b); each aircraft (1, 1') of the series comprises a module (110, 120, 130, 140) associated with a respective architecture and interfaced with said core (100).

7. 发明申请

WO2022263947A1 CONVERTIBLE AIRCRAFT CAPABLE OF HOVERING 审中-公开
公开(公告)号：WO2022263947A1
公开(公告)日：2022-12-22
申请号：PCT/IB2022/054828
申请日：2022-05-24
申请人： LEONARDO S.P.A
发明人： BIANCO MENGOTTI, Riccardo
IPC分类号： B64C27/28 , B64C29/00
摘要： 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).

8. 发明申请

WO2020003240A1 TAIL SITTER 审中-公开
公开(公告)号：WO2020003240A1
公开(公告)日：2020-01-02
申请号：PCT/IB2019/055517
申请日：2019-06-28
申请人： LEONARDO S.P.A.
发明人： BIANCO MENGOTTI, Riccardo
IPC分类号： B64C29/02 , B64C39/02 , B64C39/06 , B64C39/08 , B64D27/02 , G05D1/08
摘要： A tail sitter aircraft (1') is described that comprises: a fuselage (2) arranged vertically in a take-off/landing position and transversely to a vertical direction in a cruising position of the aircraft; a single wing (4); at least two first engines (15a, 15b) configured to exert respective first thrusts directed along respective first axes (A) on the tail sitter; and at least two second engines (15c, 15d) rotating about respective second axes (A) arranged above said first axes (A) of the first engines (15a, 15b), with reference to said cruising position; the at least two second engines being configured to exert respective second thrusts directed along respective second axes (A) on the tail sitter (1'); the first and second engines being carried by the single wing; the single wing comprises a first portion (5) and a second portion (6) mutually staggered from one another; the second portion being arranged above said first portion, with reference to said cruising position; said first portion comprises two half-wings, extending from opposite lateral sides of the fuselage; the wing further comprises a third portion (30) arranged below said first portion (5) with reference to said cruising position of said aircraft.

9. 发明申请

WO2021124213A1 CONVERTIPLANE 审中-公开
公开(公告)号：WO2021124213A1
公开(公告)日：2021-06-24
申请号：PCT/IB2020/062130
申请日：2020-12-17
申请人： LEONARDO S.P.A.
发明人： BIANCO MENGOTTI, Riccardo , BRUGHERA, Paolo , SAMPUGNARO, Luca , CASSINELLI, Carlo
IPC分类号： B64C29/00 , B64D27/14 , B64C39/12 , B64D27/24 , B64C3/56 , B64D27/12 , B64C1/14 , B64D1/06 , B64D47/08 , B64D7/06 , B64D27/02 , B64C1/1415 , B64C29/0033 , B64D2027/026
摘要： A convertiplane (1, 1', 1'') is described that comprises: a fuselage (2), having a first longitudinal axis (A) and, in turn, comprising a nose (12) and a tail portion (13); a pair of wings (3) arranged on respective opposite sides of the fuselage (2), carrying respective rotors (5) and generating a lift value; and a pair of engines (4) operatively connected to respective rotors (5); each rotor (5) comprising a mast (9) rotatable about a second axis (B) between a helicopter configuration and an aeroplane configuration; each rotor (4) is interposed between the fuselage (2) and the relative rotor (5) along the direction of extension of the relative wing (3).

10. 发明申请

WO2021124207A8 CONVERTIPLANE 审中-公开
公开(公告)号：WO2021124207A8
公开(公告)日：2021-06-24
申请号：PCT/IB2020/062120
申请日：2020-12-17
申请人： LEONARDO S.P.A.
发明人： BIANCO MENGOTTI, Riccardo , CASSINELLI, Carlo , SCANDROGLIO, Alessandro , BAVETTA, Andrea , BRUGHERA, Paolo , SAMPUGNARO, Luca
IPC分类号： B64C27/28 , B64C39/12
摘要： A convertiplane (1, 1', 1 '') is described that comprises a fuselage (2), having a first longitudinal axis (A), with a nose (12) and a tail portion (13); a pair of wings (3) arranged on respective opposite sides of said fuselage (2), carrying respective rotors (5); a pair of engines (4) operatively connected to respective said rotors (5); at least one first lifting surface (19, 16) arranged on said tail portion (13); and a pair of canards (14) arranged on said nose (12) of said fuselage (2) and defining respective second lifting surfaces adapted to generate a third lift/negative lift value; each rotor (5) comprising a mast (9) rotatable about a second axis (B) and about an relative third axis (E) transversal to said second axis (B) and with respect to the fuselage (2), so as to set said convertiplane (1, 1', 1'') between a helicopter configuration and an aeroplane configuration; each second axis (B), in use, being transversal to the first axis (A) of said convertiplane (1, 1', 1'') in said helicopter configuration and being parallel to said first axis (A) in said aeroplane configuration.

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