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57 条记录 (耗时 0.01 秒)

    Sinkless thermoelectric energy generator
    23.
    发明公开
    Sinkless thermoelectric energy generator 审中-公开
    无散热片的热电发电机

    公开(公告)号：EP2482352A3

    公开(公告)日：2013-08-21

    申请号：EP12250018.4

    申请日：2012-02-01

    申请人： Simmonds Precision Products, Inc.

    发明人： Kline, Bruce R.

    IPC分类号： H01L35/30 ,  B64C1/40 ,  B64C1/38 ,  B64D41/00

    CPC分类号： H01L35/30 ,  B64C1/38 ,  B64D41/00 ,  Y02T50/53

    摘要： Disclosed is a sinkless electric generator for generating electrical power from temperature cycles encountered by the structure of an aircraft. The sinkless electric generator includes a thermoelectric generator which is in thermal contact with the structure of the aircraft (e.g., the aircraft's skin); an insulated housing containing a thermal mass; and a circuit for providing the energy generated by the thermoelectric generator during the temperature cycles encountered by the structure of the aircraft to a device. The insulated housing is positioned in thermal contact with the thermoelectric generator; wherein during the temperature cycles encountered by the structure of the aircraft, energy is created by the thermoelectric generator when heat is released from the thermal mass contained within the housing through the thermoelectric generator to the aircraft's structure and when heat is supplied from the aircraft's structure through the thermoelectric generator to the thermal mass.

    Method and assembly for attaching components
    24.
    发明公开
    Method and assembly for attaching components 审中-公开
    Verfahren und Anordnung zur Befestigung von Bauteilen

    公开(公告)号：EP2532585A2

    公开(公告)日：2012-12-12

    申请号：EP12170610.5

    申请日：2012-06-01

    申请人： United Technologies Corporation

    发明人： Twelves, Wendell V. ,  Sinnamon, Kathleen E.

    IPC分类号： B64C13/40

    CPC分类号： F16B5/0241 ,  B64C1/06 ,  B64C1/38 ,  B64C9/02 ,  B64F5/00 ,  Y10T29/49826 ,  Y10T403/21 ,  Y10T403/217

    摘要： An example adjustable linking member (22) of a mounting assembly (20) includes a first attachment portion (24) and a second attachment portion (26). The first attachment portion (24) connects a linking member (22) to a first component (12). The second attachment portion (26) connects the linking member (22) to a second component (14). A variable portion (36) of the adjustable linking member (22) varies a distance between the first attachment portion (24) and the second attachment portion (26) in a first direction when heated. The variable portion (36) varies the distance between the first attachment portion (24) and the second attachment portion (26) in a second direction when cooled. The first direction is opposite the second direction.

    摘要翻译： 安装组件（20）的示例性可调节连接构件（22）包括第一附接部分（24）和第二附接部分（26）。 第一附接部分（24）将连接部件（22）连接到第一部件（12）。 第二连接部分（26）将连接部件（22）连接到第二部件（14）。 可调连接构件（22）的可变部分（36）在加热时沿第一方向改变第一附接部分（24）和第二附接部分（26）之间的距离。 当冷却时，可变部分（36）在第二方向上改变第一附接部分（24）和第二附接部分（26）之间的距离。 第一个方向与第二个方向相反。

    COOLING SYSTEM FOR AN AIRCRAFT, AIRCRFT COMPRISING THE COOLING SYSTEM AND COOLING METHOD
    25.
    发明公开
    COOLING SYSTEM FOR AN AIRCRAFT, AIRCRFT COMPRISING THE COOLING SYSTEM AND COOLING METHOD 审中-公开
    冷却系统一个平面上，冷却系统综合的飞机和冷却过程

    公开(公告)号：EP1928734A1

    公开(公告)日：2008-06-11

    申请号：EP05786534.7

    申请日：2005-09-20

    申请人： Volvo Aero Corporation

    发明人： MÅRTENSSON, Hans ,  HELLGREN, Anders

    IPC分类号： B64C1/38 ,  B64D7/00 ,  F41H3/00

    CPC分类号： B64C1/38

    摘要： The invention relates to a cooling system (20) for an aircraft (1) comprising a cooling circuit (21) for transporting a coolant, with the cooling circuit (21) running to a component (22) in the aircraft that is heated up during flying in order to take up heat from the heated-up component via the coolant. The cooling circuit (21) runs to a jet engine (2) for propulsion of the aircraft in order to release heat to a flow of gas (IV) in the jet engine via the coolant.

    METHODS AND SYSTEMS FOR APPLYING AERODYNAMICALLY FUNCTIONAL COATINGS TO A SURFACE
    30.
    发明授权
    METHODS AND SYSTEMS FOR APPLYING AERODYNAMICALLY FUNCTIONAL COATINGS TO A SURFACE 有权
    用于将空气动力学功能涂层应用于表面的方法和系统

    公开(公告)号：EP2991901B1

    公开(公告)日：2018-02-28

    申请号：EP14730637.7

    申请日：2014-04-30

    申请人： The Boeing Company

    发明人： BERRY, Douglas H. ,  DAVIS, Scott A.

    IPC分类号： B64F5/00

    CPC分类号： B05D1/32 ,  B05D3/108 ,  B05D3/12 ,  B05D5/00 ,  B05D5/065 ,  B05D7/57 ,  B05D2202/00 ,  B64C1/38 ,  B64C3/36 ,  B64C5/02 ,  B64C7/02 ,  B64C23/065 ,  Y10T428/24628

    摘要： An aero-contoured coating system is provided. The system has an aerodynamically functional coating having at least one or more color layers, one or more first clearcoat layers over the color layer(s) to obtain a pre-aero-contoured coating, the one or more first clearcoat layers configured for abrasion and aero-contouring to obtain an aero-contoured surface, and one or more additional clearcoat layers over the aero-contoured surface. The system further has a structure having a prepared and primed substrate surface with a primer layer. The system further has an aero-contouring device to abrade a plurality of flow surfaces on a pre-aero-contoured coated surface and to mechanically aero-contour a plurality of coating edges to reduce one or more coating edge peaks and coating edge angles of abutting coating edges between the one or more color layers. The system further has one or more masking elements for masking the one or more color layers.