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    CRYOGENIC FUEL SYSTEM WITH AUXILIARY POWER PROVIDED BY BOIL-OFF GAS
    1.
    发明申请
    CRYOGENIC FUEL SYSTEM WITH AUXILIARY POWER PROVIDED BY BOIL-OFF GAS 审中-公开
    具有辅助电力的低温燃料系统由锅炉提供

    公开(公告)号：WO2014130124A3

    公开(公告)日：2014-11-27

    申请号：PCT/US2013072843

    申请日：2013-12-03

    Applicant: GEN ELECTRIC

    Inventor： GERSTLER WILLIAM DWIGHT ,  HUDY LAURA MICHELE ,  KALRA CHIRANJEEV

    IPC: B64D37/30 ,  B64D41/00

    CPC classification number: F17C9/04 ,  B64D37/00 ,  B64D37/30 ,  B64D41/00 ,  F01K25/08 ,  F17C9/00 ,  F17C13/005 ,  F17C13/02 ,  F17C13/08 ,  F17C13/083 ,  F17C2221/033 ,  Y02T50/44

    Abstract: A system in one embodiment includes a detection unit (116), a boil- off auxiliary power unit (140), and a controller (190). The detection unit is configured to detect a characteristic of a boil-off gas stream (123) from a cryotank (110) configured to hold a cryogenic fluid. The boil-off auxiliary power unit (140) is configured to receive the boil-off gas stream (123) and use the boil-off gas stream to provide auxiliary power to a vehicle system. The controller (190) is configured to acquire information from the detection unit (116) corresponding to the characteristic; determine, using the information acquired from the detection unit, an available boil-off auxiliary energy that is available from the boil-off auxiliary power unit; determine a mode of operation of the vehicle system; determine a required auxiliary energy for the vehicle system; and to operate the auxiliary power unit based on the available boil-off auxiliary energy, the mode of operation, and the required auxiliary energy.

    Abstract translation: 一个实施例中的系统包括检测单元（116），蒸发辅助动力单元（140）和控制器（190）。 检测单元被配置为从构造成保持低温流体的低温槽（110）检测蒸发气流（123）的特性。 蒸发辅助动力单元（140）构造成接收蒸发气体流（123）并使用蒸发气体流向车辆系统提供辅助动力。 所述控制器（190）被配置为从所述检测单元（116）获取与所述特性对应的信息; 确定使用从所述检测单元获取的信息可用于从所述蒸发辅助动力单元获得的可用的沸腾辅助能量; 确定车辆系统的运行模式; 确定车辆系统所需的辅助能量; 并根据可用的沸腾辅助能量，操作模式和所需的辅助能量来操作辅助动力单元。

    RUBSTRIP WITH INTEGRAL LIGHTING FOR POSSIBLE USE IN AN AIRCRAFT
    4.
    发明申请
    RUBSTRIP WITH INTEGRAL LIGHTING FOR POSSIBLE USE IN AN AIRCRAFT 审中-公开
    具有集成照明的RUBSTRIP可在飞机上使用

    公开(公告)号：WO2014028570A1

    公开(公告)日：2014-02-20

    申请号：PCT/US2013/054858

    申请日：2013-08-14

    Applicant: IDD AEROSPACE CORPORATION

    Inventor： DAOUT, Jean-marie ,  CHEUNG, Tak, Fu ,  JIN, Zhao ,  DEBUIRE, Laurent, Daniel, Pierre

    IPC: B64D11/00

    CPC classification number: F24C15/00 ,  B64D11/00 ,  B64D11/04 ,  B64D37/30 ,  B64D47/02 ,  Y02T50/46 ,  Y10T29/49826

    Abstract: A rubstrip for protecting an exposed surface, such as a surface in the interior of an aircraft. The rubstrip is configured to house a light source within its interior. In some embodiments, an exterior of the rubstrip is formed with at least one passageway configured to emit light from the light source. The rubstrip is configured both to protect the surface from damage and to protect the housed light source from damage.

    Abstract translation: 用于保护暴露表面（例如飞机内部的表面）的橡皮筋。 橡皮圈被配置为在其内部容纳光源。 在一些实施例中，所述橡皮条的外部形成有至少一个经配置以从所述光源发射光的通道。 橡皮圈配置为保护表面免受损坏，并保护收纳的光源免受损坏。

    HYDROGEN POWERED AIRCRAFT
    6.
    发明申请
    HYDROGEN POWERED AIRCRAFT 审中-公开
    氢动力飞机

    公开(公告)号：WO2005084156A3

    公开(公告)日：2006-02-16

    申请号：PCT/US2004019746

    申请日：2004-06-21

    Applicant: AEROVIRONMENT INC

    Inventor： MACCREADY PAUL B ,  HIBBS BART D ,  SWANSON KYLE D ,  CURTIN ROBERT F

    IPC: B64C1/26 ,  B64C3/10 ,  B64C3/14 ,  B64C9/24 ,  B64C39/02 ,  B64C39/10 ,  B64D27/02 ,  B64D27/24 ,  B64D37/30 ,  B64D27/00

    CPC classification number: B64C1/26 ,  B64C3/10 ,  B64C3/14 ,  B64C9/24 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/187 ,  B64D27/02 ,  B64D27/24 ,  B64D37/30 ,  B64D2041/005 ,  Y02T50/12 ,  Y02T50/32 ,  Y02T50/44 ,  Y02T50/64 ,  Y02T90/36

    Abstract: Disclosed is an aircraft, configured to have a wide range of flight speeds, consuming low levels of power for an extended period of time, while supporting a communications platform with an unobstructed downward-looking view. The aircraft includes an extendable slat at the leading edge of the wing, and a reflexed trailing edge. The aircraft comprises a flying wing extending laterally between two ends and a center point. The wing is swept and has a relatively constant chord. The aircraft also includes a power module configured to provide power via a fuel cell. The fuel cell stores liquid hydrogen as fuel, but uses gaseous hydrogen in the fuel cell. A fuel tank heater is used to control the boil-rate of the fuel in the fuel tank. The fuel cell compresses ambient air for an oxidizer, and operates with the fuel and oxidizer at pressures below one atmosphere. The aircraft of the invention includes a support structure including a plurality of supports, where the supports form a tetrahedron that affixes to the wing.

    Abstract translation: 公开了一种被配置为具有宽范围的飞行速度的飞机，在延长的时间段内消耗低水平的电力，同时以无阻碍的向下观看的方式支持通信平台。 飞机在机翼的前缘包括一个可延伸的板条，以及一个反光后缘。 飞机包括在两端之间横向延伸的飞翼和中心点。 机翼被扫掠并具有相对恒定的和弦。 飞机还包括被配置为经由燃料电池提供动力的功率模块。 燃料电池将液态氢作为燃料储存，而在燃料电池中使用气态氢。 燃料箱加热器用于控制燃料箱中燃料的沸腾率。 燃料电池压缩氧化剂的环境空气，并在低于一个大气压的燃料和氧化剂下操作。 本发明的飞行器包括支撑结构，该支撑结构包括多个支撑件，其中支撑件形成固定在机翼上的四面体。

    AIRCRAFT AND METHOD OF MANAGING EVAPORATED CRYOGENIC FUEL
    8.
    发明申请
    AIRCRAFT AND METHOD OF MANAGING EVAPORATED CRYOGENIC FUEL 审中-公开
    飞机和蒸气冷冻燃料的管理方法

    公开(公告)号：WO2014105333A1

    公开(公告)日：2014-07-03

    申请号：PCT/US2013/071806

    申请日：2013-11-26

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： EPSTEIN, Michael, Jay ,  DELGADO Jr., Adon ,  WEISGERBER, Robert, Harold

    IPC: B64D37/30

    CPC classification number: B64D37/30 ,  B64D37/02 ,  Y02T50/44 ,  Y02T90/44

    Abstract: A method of managing evaporated cryogenic fuel in a storage tank of a cryogenic fuel system of an aircraft and an aircraft having at least one turbine engine providing propulsive force for the aircraft and a cryogenic fuel system including a passively cooled cryogenic fuel storage tank located within the aircraft, a pressure vent (501) fluidly coupled to the cryogenic fuel storage tank and exhausting evaporated gas from the cryogenic fuel to define a natural gas vent stream, and a catalytic converter (508) fluidly coupled to the pressure vent.

    Abstract translation: 管理飞机和航空器的低温燃料系统的储罐中的蒸发的低温燃料的方法，该飞行器具有至少一个涡轮发动机为飞行器提供推进力，而低温燃料系统包括被动冷却的低温燃料储存箱 飞行器，流体耦合到低温燃料储罐的压力通风口（501），并且从低温燃料排出蒸发气体以限定天然气排放流;以及流体耦合到压力通风口的催化转化器（508）。

    DOUBLE DEEP, SINGLE WIDTH OVENS FOR USE IN AIRCRAFT GALLEYS
    9.
    发明申请
    DOUBLE DEEP, SINGLE WIDTH OVENS FOR USE IN AIRCRAFT GALLEYS 审中-公开
    双重深度，单机宽度在飞机上使用

    公开(公告)号：WO2014027325A2

    公开(公告)日：2014-02-20

    申请号：PCT/IB2013/056647

    申请日：2013-08-14

    Applicant: INTERTECHNIQUE

    Inventor： LEE, Thomas Marks

    IPC: B64D11/04

    CPC classification number: F24C15/00 ,  B64D11/00 ,  B64D11/04 ,  B64D37/30 ,  B64D47/02 ,  Y02T50/46 ,  Y10T29/49826

    Abstract: Embodiments of the present invention provide double deep, single width ovens for use in aircraft galleys. The ovens are particularly beneficial as they do not change current catering process or equipment, leading to their ease of acceptability and use in the airline galley design and development industry. The ovens may be used with two standard 32-meal carriers, such that the carriers are positioned front to back in the oven. Alternatively, 64-meal carriers may be developed that fit into the double deep oven as well.

    Abstract translation: 本发明的实施例提供用于飞机厨房的双深度单宽度烤箱。 烤箱是特别有利的，因为它们不改变现有的饮食过程或设备，导致它们在航空厨房设计和开发行业中易于接受和使用。 烤箱可以与两个标准的32餐载物一起使用，使得载体位于烘箱中的前后。 或者，可以开发适合于双深度烤箱的64餐载体。

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