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    Surface deicing device configured not to generate electromagnetic interference
    1.
    发明授权
    Surface deicing device configured not to generate electromagnetic interference 有权

    公开(公告)号：US11358726B2

    公开(公告)日：2022-06-14

    申请号：US16253397

    申请日：2019-01-22

    申请人： Airbus Operations SAS

    发明人： Jonathan Carcone ,  Pierre-Louis Roux

    IPC分类号： B64D15/06 ,  B64D15/22 ,  B64D15/12 ,  B64D15/02 ,  B64D15/04

    摘要： A device for deicing a wall of an aircraft, comprising a closed circuit. The closed circuit comprises at least one condenser, positioned in the environment of the wall that is to be deiced, and in which a heat-transfer fluid condenses, generating energy in the form of latent heat which is transmitted to the wall that is to be deiced, at least one evaporator positioned in the environment of a heat source sited remotely with respect to the wall, and in which the heat-transfer fluid evaporates, absorbing energy in the form of latent heat coming from the heat source. At least part of the closed circuit is facing, in contact with, or positioned in, the wall that is to be deiced, being made of a material transparent to electromagnetic fields.

    OIL COOLER INTEGRATED INTO THE PYLON
    4.
    发明申请
    OIL COOLER INTEGRATED INTO THE PYLON 审中-公开
    油冷却器集成在PYLON中

    公开(公告)号：US20170066540A1

    公开(公告)日：2017-03-09

    申请号：US15255043

    申请日：2016-09-01

    申请人： SAFRAN AIRCRAFT ENGINES

    发明人： Kevin Morgane LEMARCHAND

    IPC分类号： B64D27/26 ,  F01D25/20 ,  B64D33/08 ,  B64D15/06 ,  F02C7/20 ,  B64D27/20

    CPC分类号： B64D27/26 ,  B64D15/06 ,  B64D27/20 ,  B64D33/08 ,  B64D2027/266 ,  F01D25/20 ,  F02C7/20 ,  F05D2220/323

    摘要： The invention relates to a suspension pylon comprising: at least one arm (3) for suspending a propulsion unit (4) from the fuselage (2) of an airplane (1), an oil exchange circuit (70) configured to be connected, on the one hand, to an oil pump (5) in the fuselage (2) and on the other hand, to the propulsion unit (4) the arm (3) whereof provides for suspension, said circuit (70) comprising a feed line (72) and a return line (74), which both extend inside said arm (3), an intermediate shaft (6) which extends in said arm (3), said shaft being configured, on the one hand, to be driven by the propulsion unit (4) the arm (3) whereof provides for suspension and, on the other hand, to drive the oil pump (5) in the fuselage (2), wherein the arm (3) has a structure adapted for cooling the oil exchange circuit at the arm (3).

    AEROSPACE PLANE SYSTEM
    5.
    发明申请
    AEROSPACE PLANE SYSTEM 审中-公开
    航空平面系统

    公开(公告)号：US20160152318A1

    公开(公告)日：2016-06-02

    申请号：US15017462

    申请日：2016-02-05

    申请人： Commercial Aerospace Plane Pty Limited

    发明人： Nick Alexander

    IPC分类号： B64C1/26 ,  B64C3/32 ,  B64C5/08 ,  B64C9/00 ,  B64D37/34 ,  B64C25/34 ,  B64C39/12 ,  B64D15/06 ,  B64D27/18 ,  B64C3/10 ,  B64C15/02

    CPC分类号： B64D37/34 ,  B64C3/10 ,  B64C3/32 ,  B64C15/02 ,  B64C30/00 ,  B64C39/12 ,  B64D27/18 ,  B64D31/00 ,  B64D2033/022 ,  B64D2033/026 ,  Y02T50/12 ,  Y02T50/44

    摘要： An aerospace plane having an elongate body supporting a pair of wings each having at least two angled, trailing edge portions. The pair of wings are adapted to extend away from the elongated body in opposing directions. A landing gear assembly is operatively associated with the elongated body to be moveable from a retracted position where the landing gear assembly is substantially locatable within the elongated body and an extended position where the landing gear assembly extends at least partially away from the elongated body. At least one engine adapted to generate thrust. At least one stabilizer adapted to assist with movement of the aerospace plane during flight. The at least one engine is located at least partially within an intake housing adapted to direct air into said at least one engine. The intake housing having at least one inlet door adapted to move from a fully open position, which allows air to pass into the engine, to a sealingly closed position which prevents air from flowing into the engine, when the engine is shut down during flight.

    摘要翻译： 一种具有支撑一对翼的细长主体的航空航天飞机，每个翼具有至少两个成角度的后缘部分。 这对翼适于在相反的方向上延伸离开细长体。 起落架组件可操作地与细长主体相关联，以从起落架组件基本上可定位在细长主体内的缩回位置移动，以及伸出位置，起落架组件至少部分地远离细长主体延伸。 至少一个适于产生推力的发动机。 至少一个稳定器适于在飞行期间协助航空航天飞机的运动。 所述至少一个发动机至少部分地位于适于将空气引导到所述至少一个发动机内的进气室内。 进气壳体具有至少一个入口门，其适于从允许空气进入发动机的完全打开位置移动到密封关闭位置，当发动机在飞行期间关闭时防止空气流入发动机。

    Icing protection system for an aircraft and method for operating an icing protection system
    6.
    发明授权
    Icing protection system for an aircraft and method for operating an icing protection system 有权
    用于飞机的结冰保护系统和运行结冰保护系统的方法

    公开(公告)号：US09267715B2

    公开(公告)日：2016-02-23

    申请号：US13754027

    申请日：2013-01-30

    申请人： Airbus Operations GmbH

    发明人： Tobias Scheibert

    IPC分类号： F25B41/00 ,  F25B21/04 ,  H01M8/04 ,  B64D15/04 ,  B64D15/02 ,  B64D15/06 ,  B64D41/00

    CPC分类号： F25B21/04 ,  B64D15/02 ,  B64D15/04 ,  B64D15/06 ,  B64D2041/005 ,  F25D21/04 ,  H01M8/04059 ,  Y02T90/36

    摘要： An icing protection system comprises a fuel cell, an evaporative cooling system, a thermal deicing device, a control unit and a device for measuring the pressure in the evaporative cooling system. The evaporative cooling system is in thermal contact with the fuel cell and with the thermal deicing device in order to conduct heat from the fuel cell to the thermal deicing device. The control unit controls the electrical power demanded from the evaporatively cooled fuel cell in dependence on a deviation of the pressure measured by the pressure measuring device from a predetermined NOMINAL pressure. In this way, an energetically very efficient and very well controllable icing protection system is made available that can be operated without bleed air supplied by engines or electrical energy provided by engine generators.

    摘要翻译： 结冰保护系统包括燃料电池，蒸发冷却系统，热除冰装置，控制单元和用于测量蒸发冷却系统中的压力的​​装置。 蒸发冷却系统与燃料电池和热除冰装置热接触，以将热量从燃料电池传导到热除冰装置。 控制单元根据由压力测量装置测量的压力与预定的NOMINAL压力的偏差来控制从蒸发冷却的燃料电池所需的电力。 以这种方式，可以获得能够非常有效且非常好地控制的结冰保护系统，其可以在发动机或由发动机发电机提供的电能提供的排放空气下运行。

    Methods and systems for rain removal and de-icing of monolithic windshields
    7.
    发明申请
    Methods and systems for rain removal and de-icing of monolithic windshields 审中-公开
    单片挡风玻璃除雨除冰的方法和系统

    公开(公告)号：US20060097111A1

    公开(公告)日：2006-05-11

    申请号：US10958240

    申请日：2004-10-04

    申请人： Jeffrey Wood ,  Terry Sewell

    发明人： Jeffrey Wood ,  Terry Sewell

    IPC分类号： B64D15/06

    CPC分类号： B64C1/1476 ,  B64D15/02

    摘要： Systems and methods for providing rain and ice removal on a windshield are. provided. The system may be implemented on a vehicle, such as an aircraft. In one embodiment, a system includes an injection molded windshield and a frame coupled to the injection-molded windshield and to the vehicle. The frame includes a channel that directs at least one of air or fluid onto an exterior surface of the windshield. The frame includes one or more one-way check valves. A fluid pump pumps fluid through the channel and onto the windshield. A reservoir stores de-icing fluid that is retrieved by the fluid pump. Air sources pump air through the channel and onto the one or more windshields. A controlling device controls the fluid pump or the air sources.

    摘要翻译： 在挡风玻璃上提供雨淋和除冰的系统和方法。 提供。 该系统可以在诸如飞行器的车辆上实现。 在一个实施例中，系统包括注塑挡风玻璃和耦合到注塑挡风玻璃和车辆的框架。 框架包括将空气或流体中的至少一个引导到挡风玻璃的外表面上的通道。 框架包括一个或多个单向止回阀。 流体泵将液体通过通道泵送到挡风玻璃上。 储存器存储由流体泵取回的除冰液。 空气源将空气通过通道泵送到一个或多个挡风玻璃上。 控制装置控制流体泵或空气源。

    Deicing fluid recovery system especially adapted for aircraft deicing apparatus
    8.
    发明授权
    Deicing fluid recovery system especially adapted for aircraft deicing apparatus 失效
    除冰液回收系统特别适用于飞机除冰装置

    公开(公告)号：US5904321A

    公开(公告)日：1999-05-18

    申请号：US932782

    申请日：1992-08-19

    申请人： Dennis Michael Cox ,  Joe Allen Cox ,  Richard Wayne Palmer ,  James Donald Holbert

    发明人： Dennis Michael Cox ,  Joe Allen Cox ,  Richard Wayne Palmer ,  James Donald Holbert

    IPC分类号： B64F5/00 ,  B64D15/06

    CPC分类号： B64F5/0054 ,  B64F5/0063 ,  Y02P70/585

    摘要： A deicing fluid recovery system for aircraft deicing apparatus includes a storage tank from which a deicing fluid/water deicing mixture is pumped through a line heater to a deicing fluid distribution and collection zone for application to the wings and fuselage of aircraft. Expended deicing fluid is collected in a drainage system incorporated into a concrete or asphalt pad and directed to a sump. Upon accumulation of a sufficient quantity, the diluted used deicing fluid is pumped to a sludge tank. Solids and free water are separated by settling and filtration processes in the sludge tank. The filtered deicing fluid mixture is heated through sequential heat exchangers and directed to a regenerator. The deicing fluid mixture is leaned by a dehydration process in the regenerator in which the mixture is heated and compressed air is injected to exhaust water from a stripping column. The lean deicing fluid flows over an overflow weir into an accumulator. The heated and leaned deicing fluid mixture then is passed back through the sequential heat exchangers, as a heat source, and pumped back into the storage tank for subsequent reuse.

    摘要翻译： 一种用于飞机除冰装置的除冰液回收系统包括储存罐，除冰流体/除冰混合物从该储罐通过管线加热器泵送到除冰流体分配和收集区，以应用于飞行器的机翼和机身。 消除的除冰液被收集在结合到混凝土或沥青垫中的排水系统中并且被引导到贮槽。 在积聚足量的情况下，将稀释后的除冰液泵送到污泥槽。 固体和游离水通过污泥池中的沉淀和过滤过程分离。 过滤的除冰液混合物通过顺序热交换器加热并引导至再生器。 除冰液体混合物通过再生器中的脱水过程倾斜，其中混合物被加热并且压缩空气被注入以从汽提塔排出水。 稀薄的除冰液在溢流堰上流入蓄能器。 然后将加热和倾斜的除冰液混合物作为热源通过顺序热交换器，并将其泵送回储罐以供后续再利用。