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322 条记录 (耗时 0.023 秒)

    ROTOR FOR A HOVER-CAPABLE AIRCRAFT
    21.
    发明公开
    ROTOR FOR A HOVER-CAPABLE AIRCRAFT 审中-公开

    公开(公告)号：EP3766778A1

    公开(公告)日：2021-01-20

    申请号：EP19187399.1

    申请日：2019-07-19

    申请人： LEONARDO S.p.A.

    发明人： BOTTASSO, Luigi ,  FOSCO, Ermanno ,  PISANI, Paolo ,  VINCENZO, Francesco ,  ROSA, Francesco ,  BRAGHIN, Francesco ,  CAZZULANI, Gabriele ,  CINQUEMANI, Simone

    IPC分类号： B64C27/00

    摘要： A rotor (3, 3', 3") for an aircraft (1) is described that has a mast (150), an attenuating device (7, 7', 7") to attenuate the transmission of vibrations from the mast (150) in a plane orthogonal to the first axis (A); and a transmission device (15) interposed between the mast (150) and the attenuating device (7, 7', 7"); the attenuating device (7, 7', 7") comprises a first and a second mass unit (8, 9) with a first and a second mass (10, 11) rotatable about the first axis (A) with a first and a second rotational speed ((N-1)*Ω; (N+1)*Ω); (N+1)*Ω; (N-1)*Ω)), two control units (40, 40') operable to cause an additional rotation of at least one of the first and second masses (10, 11); and a first and a second support assembly (41, 41'; 42, 42') carrying the first and second masses (10; 11); each control unit (40, 40') controls the angle between the first and second masses (10, 11) and each control unit (40, 40') comprises: a belt (50) coupled to the support assembly (41, 41'; 42, 42') and a drive unit (51, 51') coupled to the first belt (50), to cause the rotation of the first support assembly (41, 41'; 42, 42') with respect to said transmission device (15).

    VERTICAL TAKE-OFF AND LANDING AIRCRAFT AND RELATED CONTROL METHOD
    27.
    发明公开
    VERTICAL TAKE-OFF AND LANDING AIRCRAFT AND RELATED CONTROL METHOD 审中-公开

    公开(公告)号：EP3730404A1

    公开(公告)日：2020-10-28

    申请号：EP19170690.2

    申请日：2019-04-23

    申请人： LEONARDO S.p.A.

    发明人： BIANCO MENGOTTI, Riccardo

    IPC分类号： B64C29/00 ,  B64C27/20 ,  B64C27/26

    摘要： An aircraft (1, 1', 1") capable of vertical take-off and landing is described, comprising a first propulsion unit (6a, 6b, 6c, 6d, 6e, 6f; 6a, 6b, 6g', 6h', 6c, 6d, 6e, 6i', 6j', 6f; 6a, 6c; 6d, 6f) configured to generate a first thrust (T1, T2, T3, T4, T5, T6; T1, T2, T7, T8, T3, T4, T5, T9, T10, T6; T1, T3, T4, T6) directed along a first axis (E, F, G, H, I, J; E, F, K, L, G, H, I, M, N, J; E, G, H, J); a second propulsion unit (6a, 6b, 6c, 6d, 6e, 6f; 6a, 6b, 6g', 6h', 6c, 6d, 6e, 6i', 6j', 6f; 6a, 6c; 6d, 6f) configured to generate a second thrust (T1, T2, T3, T4, T5, T6; T1, T2, T7, T8, T3, T4, T5, T9, T10, T6; T1, T3, T4, T6) directed along a second axis (E, F, G, H, I, J; E, F, K, L, G, H, I, M, N, J; E, G, H, J) ; the first propulsion unit and the second propulsion unit (6a, 6b, 6c, 6d, 6e, 6f; 6a, 6b, 6g', 6h', 6c, 6d, 6e, 6i', 6j', 6f; 6a, 6c; 6d, 6f) can be operated independently of one another; the first axis and second axis (E, F, G, H, I, J; E, F, K, L, G, H, I, M, N, J; E, G, H, J) are inclined to one another with respect to a first longitudinal direction (Y) of the aircraft (1, 1', 1"); the first axis and the second axis (E, F, G, H, I, J; E, F, K, L, G, H, I, M, N, J; E, G, H, J) are fixed with respect to the aircraft (1, 1', 1'').

    VALVE SYSTEM FOR AN ELECTROCHEMICAL POWER SOURCE, IN PARTICULAR FOR AN UNDERWATER VESSEL, AND ITS ELECTROCHEMICAL POWER SOURCE
    28.
    发明公开
    VALVE SYSTEM FOR AN ELECTROCHEMICAL POWER SOURCE, IN PARTICULAR FOR AN UNDERWATER VESSEL, AND ITS ELECTROCHEMICAL POWER SOURCE 审中-公开

    公开(公告)号：EP3709395A1

    公开(公告)日：2020-09-16

    申请号：EP20162944.1

    申请日：2020-03-13

    申请人： LEONARDO S.p.A.

    发明人： BARTOLI, Dino ,  GASSANI, Yuri

    IPC分类号： H01M2/40 ,  H01M6/04 ,  H01M6/34

    摘要： An electrochemical-type power supply source (1) is provided with: an electrochemical stack (2) generating electric power, in the presence, internally, of electrolytic fluid, provided with a number of distinct groups of galvanic cells (4) and of a corresponding number of electrolyte inlet pipes (8) for introducing electrolyte into respective groups of galvanic cells (4) and with electrolyte outlet pipes (9) for extracting electrolyte from respective groups of galvanic cells (4); a main tank (5), fluidically coupled to the electrochemical stack and containing electrolytic fluid; and a recirculation system (6, 10), defining a circulation path of the electrolytic fluid between the main tank and the electrochemical stack. A valve system (20) that can be coupled to the electrolyte inlet and/or outlet pipes and operatively controllable to modify hydraulic and electric characteristics of the circulation path, in response to a power delivery condition by the power supply source.

    SAFETY AUXILIARY SYSTEM FOR A MODULAR BATTERY IN AN UNDERWATER VEHICLE AND CORRESPONDING BATTERY
    29.
    发明公开
    SAFETY AUXILIARY SYSTEM FOR A MODULAR BATTERY IN AN UNDERWATER VEHICLE AND CORRESPONDING BATTERY 审中-公开

    公开(公告)号：EP3694045A1

    公开(公告)日：2020-08-12

    申请号：EP20155971.3

    申请日：2020-02-06

    申请人： LEONARDO S.p.A.

    发明人： TEVENE', Bruno

    IPC分类号： H01M10/48 ,  H01M10/613 ,  H01M10/63 ,  A62C3/07

    摘要： A safety auxiliary system (10), coupled to a modular battery (2) of an underwater vehicle (1) having a number of modules (3), each provided with a plurality of cells (4), has: a first subsystem (10a), which detects conditions indicative of a thermal runaway in any of the modules (3) and manages such a thermal runaway, intervening locally on the module (3) to cool the corresponding cells (4) so that the thermal runaway is not propagated; and a second subsystem (10b), cooperating with, and operatively coupled to, the first subsystem (10a), which manages gases present in the module (3) associated with the thermal runaway, preventing them from pouring inside the underwater vehicle (1). The first subsystem (10a) is provided with a first electronic control unit (16) for each of said modules (3), and the second subsystem (10b) is provided with a second electronic control unit (16), distinct from, and operatively coupled to, the first electronic control unit (16) through a communication connection (38), so as to receive an alarm signal (S al ) upon detection of the conditions indicative of the thermal runaway in the corresponding module (3).

    AIRCRAFT
    30.
    发明公开
    AIRCRAFT 审中-公开

    公开(公告)号：EP3670340A1

    公开(公告)日：2020-06-24

    申请号：EP18215247.0

    申请日：2018-12-21

    申请人： LEONARDO S.p.A.

    发明人： PODDA, Daniele ,  GABRIELLI, Andrea ,  REGONINI, Roberto ,  MONTAGNA, Federico ,  POGGI, Stefano

    IPC分类号： B64C27/28 ,  F16C19/54 ,  F16C25/08

    摘要： An aircraft (1) is described comprising: a support element (16; 16'); a shaft (12; 12') rotating about an axis (E, E'); a pair of oblique roller bearings(17; 17') mounted so as to couple the shaft (12; 12') to the support element (16; 16') rotatingly about the axis (E, E'); the roller bearings (17; 17') comprising: respective first races (18, 19; 18', 19') cooperating radially in contact with a first component (16, 12; 16', 12') defined by one from the support element (16; 16') and the shaft (12; 12'); respective second races (19, 18; 19', 18') cooperating radially in contact with a second component (12, 16; 12', 16') defined by the other from the support element (16; 16') and the shaft (12; 12'); and respective pluralities of rolling elements (20; 20') adapted to roll on the first and second races (18, 19; 18' 19'; 19, 18; 19', 18'); the aircraft (1) further comprises a pair of preloaded elastic members (21; 21'), which couple the first races 18, 19; 18', 19') to the first component (16, 12; 16', 12') respectively, axially and in an elastically yielding manner.