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    VEHICLE
    1.
    发明申请
    VEHICLE 审中-公开

    公开(公告)号：WO2023285857A1

    公开(公告)日：2023-01-19

    申请号：PCT/IB2021/056329

    申请日：2021-07-14

    Applicant: ITALDESIGN-GIUGIARO S.P.A.

    Inventor： PIGNATALE, Domenico ,  DANNA, Fabio ,  BALLARINI, Mirko ,  MASUELLI, Stefania

    IPC: B60Q1/00 ,  F21S41/63 ,  F21S41/675

    Abstract: A vehicle (1) comprising a body (2); a light source (15); a lighting assembly (3a, 3b, 3c, 3d; 3a', 3a'') comprising, in turn, a frame (50) is described; and means for transmitting (16) the light generated by the source (15), constrained to the body (2) and configured to transmit the light from the source (15) to the lighting assembly (3a, 3b, 3c, 3d; 3a', 3a'') the source (15) and the transmission means (16) are constrained to the body (2) and external to the frame (50); the lighting assembly (3a, 3b, 3c, 3d; 3a', 3a'') an optical assembly (53, 53', 53'') configured to deflect a first light ray (23) from the source (15) and to form at least a second light ray (28, 28', 28''); the optical assembly (53, 53', 53'') comprises a first portion (55; 60'') fixed with respect to the frame (50); and a second portion (54, 56; 54, 100''), whose position is adjustable with respect to the frame (50) so as to make said second light ray (28, 28', 28'') orientable in one between a first and second planer (P, Q).

    METHOD FOR CONTROLLING AN AIRCRAFT CAPABLE OF HOVERING AND RELATIVE AIRCRAFT
    2.
    发明申请
    METHOD FOR CONTROLLING AN AIRCRAFT CAPABLE OF HOVERING AND RELATIVE AIRCRAFT 审中-公开

    公开(公告)号：WO2022029581A1

    公开(公告)日：2022-02-10

    申请号：PCT/IB2021/056978

    申请日：2021-07-30

    Applicant: LEONARDO S.P.A.

    Inventor： MEDICI, Luca ,  NANNONI, Fabio ,  BRAGHIROLI, Marco ,  COGLIATI, Andrea ,  FRATTINI, Tiziano ,  MASELLIS, Lorenzo ,  RIVIELLO, Luca ,  SCOLA, Alessandro ,  TAMBORINI, Marco ,  PIZZAGALLI, Matteo

    IPC: F02C7/36 ,  F02C3/113 ,  F02C6/02 ,  F05D2220/329 ,  F05D2270/093 ,  F05D2270/13

    Abstract: A method for controlling an aircraft (1) capable of hovering is described, comprising a first engine (10a); a second engine (10b); at least one rotor (3); and a transmission (8) interposed between the first and second engine (10a, 10b) and the rotor (3); the transmission (8) comprises a first and a second inlet (12a, 12b) connected respectively to a first outlet member (11a) of the first engine (10a) and to a second outlet member (11b) of the second engine (10b); the method comprises step i) of placing the aircraft (1) in a first configuration, in which the first and second engine (10a, 10b) make available a first and a second power value (PI, P2); or in a second configuration, in which the first engine (10a) makes available a third power value (P3) greater than the first power value (P1) to the first inlet (12a), and the second engine (10b) delivers a nil power value (P4) to the second inlet (12b); the method also comprises, characterised in that it comprises the steps of ii) detecting a series of parameters associated with the operating conditions of the aircraft (1); and iii) enabling the transition of the aircraft (1) from the first configuration to the second configuration, when the parameters assume respective first values.

    CONVERTIPLANE
    4.
    发明申请
    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

    Applicant: LEONARDO S.P.A.

    Inventor： BIANCO MENGOTTI, Riccardo ,  CASSINELLI, Carlo ,  SCANDROGLIO, Alessandro ,  BAVETTA, Andrea ,  BRUGHERA, Paolo ,  SAMPUGNARO, Luca

    IPC: B64C27/28 ,  B64C39/12

    Abstract: 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.

    MONITORING SYSTEM FOR PERISHABLE PRODUCTS
    5.
    发明申请
    MONITORING SYSTEM FOR PERISHABLE PRODUCTS 审中-公开

    公开(公告)号：WO2021005525A1

    公开(公告)日：2021-01-14

    申请号：PCT/IB2020/056419

    申请日：2020-07-08

    Applicant: PASQUI, Valentina ,  FARAN, Ori

    Inventor： PASQUI, Valentina ,  FARAN, Ori

    IPC: B41M3/14 ,  G06K19/06

    Abstract: The present invention provides a combine system in the present invention can be used as dual propose temperature monitoring indicator. The system comprises of scanning devise, QR barcode and temperature indicator providing visual characteristic, which changed depending on time and temperature after triggering, had occurred. The device is not susceptible to environmental conditions and can be stored in room temperature.

    ANTI-TORQUE ROTOR FOR A HELICOPTER
    6.
    发明申请
    ANTI-TORQUE ROTOR FOR A HELICOPTER 审中-公开

    公开(公告)号：WO2020254895A1

    公开(公告)日：2020-12-24

    申请号：PCT/IB2020/054979

    申请日：2020-05-26

    Applicant: LEONARDO S.P.A.

    Inventor： DELLI PAOLI, Michele ,  NANNONI, Fabio ,  VANNI, Roberto

    IPC: B64C27/78 ,  B64C27/82 ,  B64C27/12

    Abstract: An anti-torque rotor (4, 4') is described that comprises: a mast (6) rotatable about a first axis (A); a plurality of blades (8) extending along respective second axes (B); a control element (16) sliding along the first axis (A) with respect to the mast (6), integrally rotatable with said mast (6), and connected to said blades (8); a control rod (10) sliding axially along first axis (A) and angularly fixed with respect to said first axis (A); a connection element (17) interposed between the control rod (10) and the control element (16), sliding along the first axis (A) integrally with the control rod (10), and configured to enable the relative rotation of said control element (16) with respect to the control rod (10) about the first axis (A); and a transmission unit (45) available in an active configuration or an inactive configuration; the transmission unit (45), in turn, comprises: an annular ridge (61) axially and angularly integral with the control rod (10) and radially projecting from the control rod (10); and a seat (64) engaged by the ridge (61) and angularly integral with the control element (16).

    VEHICLE AND METHOD OF COOLING A COMPARTMENT OF SAID VEHICLE
    7.
    发明申请
    VEHICLE AND METHOD OF COOLING A COMPARTMENT OF SAID VEHICLE 审中-公开

    公开(公告)号：WO2020109889A1

    公开(公告)日：2020-06-04

    申请号：PCT/IB2019/059363

    申请日：2019-10-31

    Applicant: LEONARDO S.P.A.

    Inventor： PATRICELLI, Luca

    IPC: B64D13/08

    Abstract: An aerial, marine or land vehicle (1) comprising: a compartment (6) to be cooled; a first circuit (20) through which can pass and, in turn, comprising, a heat exchanger (22) that can be fed with the coolant and is designed to enable the coolant to release heat; a second circuit (60) that can be fed with a second flow of a heat-carrying fluid and is thermally coupled to the heat exchanger (22); and supply means (61) for supplying a mixture comprising water, inside the second flow in a position upstream of the heat exchanger (22) and spaced from the heat exchanger (22), proceeding along the feed direction of the second flow along the second circuit (60), so as to cause evaporation of the mixture and cool the second flow in the heat exchanger (22).

    TAIL SITTER
    8.
    发明申请
    TAIL SITTER 审中-公开

    公开(公告)号：WO2020003239A3

    公开(公告)日：2020-01-02

    申请号：PCT/IB2019/055514

    申请日：2019-06-28

    Applicant: LEONARDO S.P.A.

    Inventor： BIANCO MENGOTTI, Riccardo

    IPC: B64C39/06 ,  B64C39/02 ,  B64C29/02 ,  B64C39/08 ,  B64D27/02 ,  G05D1/08

    Abstract: A tail sitter aircraft (1', 1 ") is described, comprising a wing (4) with a closed front section (C); a fuselage (2), from which said wing extends; said fuselage extending parallel to a first axis (Y); said wing being a non-planar wing closed in on itself and without free ends; said wing comprising a first portion (5) projecting from said fuselage, a second portion (6) spaced from said first portion; and - a first and a second connecting section (7), which are interposed between respective ends (8, 9) of said first portion (5) and of said second portion, said first portion and said second portion being parallel to one another and extending parallel to a second axis (X) orthogonal to said first axis (Y), said first axis (Y) being arranged, in use, vertically in a take-off/landing position and inclined with respect to the vertical direction in a cruising position. Said first and a second connecting section extend parallel to a third axis (Z) orthogonal to said second axis and to said first axis, said wing comprising a third portion (30) arranged on the opposite side of said first portion with respect to said second portion and connected to said first portion at their respective ends (32, 8) by first sections (31) extending parallel to said third axis.

    STABILITY AND COMMAND AUGMENTATION SYSTEM FOR AN AIRCRAFT, AND STABILIZATION AND CONTROL METHOD OF AN AIRCRAFT
    10.
    发明申请
    STABILITY AND COMMAND AUGMENTATION SYSTEM FOR AN AIRCRAFT, AND STABILIZATION AND CONTROL METHOD OF AN AIRCRAFT 审中-公开

    公开(公告)号：WO2019069287A1

    公开(公告)日：2019-04-11

    申请号：PCT/IB2018/057759

    申请日：2018-10-05

    Applicant: LEONARDO S.P.A.

    Inventor： VANNI, Roberto ,  GAGLIOSTRO, Davide ,  CASOLA, Davide

    IPC: G05D1/08 ,  B64C13/00 ,  F15B18/00 ,  G05B13/00 ,  G05G11/00

    Abstract: A stability and command augmentation system (20) for controlling an aircraft (1), comprising: a first member (19) moveable by a pilot input device (10, 11, 15) to a first position defining a first input (xi); a second member (22) moveable to a second position associated with a second input (xd); and an adder device (21) configured to add the first and second inputs (xi, xd) and supply an output signal (xv) defining a command for an element to be controlled (9, 14) of the aircraft (1); the stability and command augmentation system (20) comprises: a casing (30), a first and a second piston (31, 32) integrally movable with one another inside the casing (30) and operatively connected to the second member (22); and control means (33) configured to exert a first force on the first piston and a second force on the second piston (31, 32); the second force is independent of the first force.

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