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2840 条记录 (耗时 0.023 秒)

    FUSELAGE FOR A CONVERTIBLE AIRCRAFT CAPABLE OF HOVERING
    81.
    发明公开
    FUSELAGE FOR A CONVERTIBLE AIRCRAFT CAPABLE OF HOVERING 审中-公开

    公开(公告)号：EP4279390A1

    公开(公告)日：2023-11-22

    申请号：EP22174037.6

    申请日：2022-05-18

    申请人： Leonardo S.p.a.

    发明人： MEDICI, Luca ,  BIANCO MENGOTTI, Riccardo ,  BAVETTA, Andrea ,  BASAGLIA, Marco

    IPC分类号： B64D27/24 ,  B64D33/08 ,  B64C29/00 ,  B64C7/00 ,  B64C1/14

    摘要： A fuselage (2, 2', 2") for a convertible aircraft (1) is described, comprising a nose (4) and a tail (5) arranged on mutually opposite sides along a first longitudinal axis (Y) of the fuselage (2); a first portion (100) and a second portion (101) arranged one after the other, proceeding along the first axis (Y) from the nose (4) towards the tail (5); and an electric power source (102) connectable with at least one electric powertrain (40a, 40b, 40c, 40d, 40e, 40f) and arranged inside the second portion (101); the first and second portion (100, 101) define respectively a first and a second section (110, 111, 111") in a plane orthogonal to the first axis (Y); the second section (111) defines at least one air intake (120) that is open towards the outside of the fuselage (2) itself and fluidically connected with the source (102) so as to convey, in use, a flow of cooling air onto the source (102) itself following the forward motion of the aircraft (1); the second section (111, 111") having a larger area than the first section (110); the air intake (120) being arranged at a sidewall (19) of the second portion (101) and externally to the first portion (100) and in a view parallel to the first axis (Y).

    BATTERY PACK AND BATTERY
    83.
    发明公开
    BATTERY PACK AND BATTERY 审中-公开

    公开(公告)号：EP4265523A1

    公开(公告)日：2023-10-25

    申请号：EP21915163.6

    申请日：2021-12-22

    申请人： Space Walker, Inc.

    发明人： ISHIDA, Kenji ,  YONEMOTO, Koichi

    IPC分类号： B64D27/24 ,  B64G1/14 ,  H01M50/213 ,  H01M50/249

    摘要： The present invention addresses the problem of improving space efficiency in placement in an aircraft. A front-side battery pack 30 is installed in a spacecraft 1 having a curved outer wall 11. The front-side battery pack 30 comprises a plurality of battery cells 31 disposed along an inner surface 11b of the outer wall 11, and cables 32 electrically and respectively connected to the plurality of battery cells 31. Each of the plurality of battery cells 31 has a first surface 31a facing the inner surface 11b of the outer wall 11, a second surface 31b on the side opposite from the first surface 31a, and side surfaces 31c connecting the first surface 31a and the second surface 31b, the battery cells 31 being disposed such that the side surfaces 31c of mutually adjacent battery cells 31 face each other. The cables 32 are arranged in gaps V formed between the side surfaces 31c of mutually adjacent battery cells 31.

    AIRCRAFT POWERPLANT(S) FOR AN AIRCRAFT WITH ELECTRIC MACHINE CONTROLLED PROPULSOR SPEED
    88.
    发明公开
    AIRCRAFT POWERPLANT(S) FOR AN AIRCRAFT WITH ELECTRIC MACHINE CONTROLLED PROPULSOR SPEED 审中-公开

    公开(公告)号：EP4253246A1

    公开(公告)日：2023-10-04

    申请号：EP23165248.8

    申请日：2023-03-29

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： ALECU, Daniel

    IPC分类号： B64D27/02

    摘要： An aircraft system (20) includes a propulsor (26), a powerplant (28) and a control system (24). The powerplant (28) is configured to output mechanical power to drive rotation of the propulsor (26). The powerplant (28) includes a heat engine (32) and an electric machine (30). The heat engine (32) is configured to provide a first portion of the mechanical power. The electric machine (30) is configured to provide a second portion of the mechanical power. The control system (24) is configured to operate the powerplant (28) to control a rotational speed of the propulsor (26) by adjusting the second portion of the mechanical power.