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    CONTROL DEVICE FOR ELECTRIC FLIGHT VEHICLE
    1.
    发明公开
    CONTROL DEVICE FOR ELECTRIC FLIGHT VEHICLE 审中-公开

    公开(公告)号：EP4442573A1

    公开(公告)日：2024-10-09

    申请号：EP22901030.1

    申请日：2022-11-07

    申请人： DENSO CORPORATION

    发明人： TAKEMURA, Yuichi ,  FUKUSHI, Masato

    IPC分类号： B64D27/24 ,  B64C27/26 ,  B64C39/02

    CPC分类号： Y02T50/60 ,  B64C27/26 ,  B64C39/02 ,  B64D27/24 ,  B64U50/37 ,  B64U10/16 ,  B64U50/19 ,  B64U30/20 ,  B64C27/08 ,  B64U50/30

    摘要： A flight control device performs flight control processing for causing an eVTOL to fly. The flight control device determines whether the eVTOL is on the ground in step S101 of the flight control processing. When the eVTOL is on the ground, the flight control device (40) acquires a temperature of a drive battery as a battery temperature (Tbt) in step S102. In step S103, the flight control device (40) determines whether the battery temperature (Tbt) is lower than a take-off permitting temperature (TA). When the battery temperature (Tbt) is lower than the take-off permitting temperature (TA), the flight control device (40) proceeds to step S104 to prohibit take-off of the eVTOL. Thereafter, the flight control device (40) performs the temperature raising control in step S105. In the temperature raising control, the temperature of the drive battery (31) is raised.

    PROPULSION SYSTEM ARRANGEMENT FOR TURBOFAN GAS TURBINE ENGINE
    2.
    发明公开
    PROPULSION SYSTEM ARRANGEMENT FOR TURBOFAN GAS TURBINE ENGINE 审中-公开

    公开(公告)号：EP4411128A3

    公开(公告)日：2024-10-09

    申请号：EP24184479.4

    申请日：2016-02-08

    申请人： RTX Corporation

    发明人： ECKETT, Christopher A. ,  SUCIU, Gabriel L.

    IPC分类号： F02K3/06 ,  F02C7/20 ,  F01D21/04 ,  F02K1/72 ,  F02K1/76 ,  F02K1/09

    CPC分类号： F02K1/09 ,  F02K1/72 ,  F02K3/06 ,  F02K1/763 ,  F01D21/045 ,  Y02T50/60

    摘要： An integrated propulsion system (10) comprises components that include a gas turbine engine (20) and a nacelle assembly (82). The nacelle assembly (82) includes a fan nacelle (86) arranged at least partially about a fan (42) and an engine. The system includes a fan section (22) at least partially defined by the fan nacelle (82), and the fan section (22) has a fan pressure ratio of less than about 1.7. The engine includes a turbine section (28) configured to drive the fan section (22) and a compressor section (24), the compressor section (24) including a first compressor (44) and a second compressor (52). An overall pressure ratio is provided by the combination of a pressure ratio across the first compressor (44) and a pressure ratio across the second compressor (52), and wherein the overall pressure ratio is greater than or equal to about 35. The fan section (22) is configured to deliver a portion of air into the compressor section (24), and a portion of air into a bypass duct, and wherein a bypass ratio, defined as a volume of air passing to the bypass duct compared to a volume of air passing into the compressor section (24), is equal to or greater than about 5.