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    SYSTEM AND METHOD FOR CUTTING COMPOSITE MATERIALS
    11.
    发明申请
    SYSTEM AND METHOD FOR CUTTING COMPOSITE MATERIALS 审中-公开

    公开(公告)号：US20170225246A1

    公开(公告)日：2017-08-10

    申请号：US15418984

    申请日：2017-01-30

    Applicant: Cessna Aircraft Company

    Inventor： Billy Joe Page

    IPC: B23D59/00 ,  B23D51/04 ,  G05B19/18 ,  B23D51/08

    CPC classification number: B23D59/002 ,  B23D45/044 ,  B23D47/04 ,  B23D51/04 ,  B23D51/08 ,  B23D59/008 ,  B27B19/006 ,  G05B19/182 ,  G05B2219/36086

    Abstract: Embodiments of this disclosure provide a system and method for cutting composite materials. The system includes a material supporting surface, an oscillating saw suspended from a rotatable head on an arm, a two-axis gimbal coupled to the rotatable head for adjusting a cutting angle of the oscillating saw, and a material clamp for clasping the composite material to prevent the composite material from slipping while being cut with the oscillating saw. An automated embodiment of the system further includes a controller for instructing the oscillating saw to cut the composite material by guiding the saw via coordinated movement of the rotatable head, the arm, and the gimbal. A method of cutting a woven composite material includes feeding the material on a support surface, providing an oscillating saw blade on a guiding mechanism, and cutting the material by moving the saw blade in a direction based on the guiding mechanism.

    FUEL TANK TUBE BONDING TAB
    13.
    发明申请
    FUEL TANK TUBE BONDING TAB 审中-公开
    燃油罐管接头

    公开(公告)号：US20160318624A1

    公开(公告)日：2016-11-03

    申请号：US15097951

    申请日：2016-04-13

    Applicant: CESSNA AIRCRAFT COMPANY

    Inventor： RICHARD A. SKIBBA ,  M. SCOTT MONTGOMERY

    IPC: B64D45/02 ,  B64D37/32 ,  H05F3/02

    CPC classification number: B64D45/02 ,  B64D37/32

    Abstract: Disclosed are systems and methods for grounding insulated P-clamps used to secure fuel conduits. To do so, one end of the device is adapted to be secured between the flanges of the P-clamp, and a second end is adapted to extend into the clamp to make electrical contact with the conduit. The device creates an electrical path to the grounded structure to which the clamp is secured.

    Abstract translation: 公开了用于固定燃料管道的绝缘P型夹具接地的系统和方法。 为了做到这一点，设备的一端适于固定在P型夹具的凸缘之间，并且第二端适于延伸到夹具中以与导管电接触。 该装置产生到固定夹具的接地结构的电路径。

    Self-centering aircraft flap position command apparatus
    15.
    发明授权
    Self-centering aircraft flap position command apparatus 有权
    自动定心飞机挡板位置指令装置

    公开(公告)号：US09327826B2

    公开(公告)日：2016-05-03

    申请号：US13660729

    申请日：2012-10-25

    Applicant: Cessna Aircraft Company

    Inventor： Ronald J. Nieman

    IPC: B64C13/04

    CPC classification number: B64C13/04 ,  Y10T74/20612

    Abstract: An apparatus for controlling positioning of flaps in an aircraft includes a shift lever movable to each of a plurality of shift lever positions to control positioning of the flaps of the aircraft to each of a respective plurality of associated flap positions. A shift lever indexing plate includes a plurality of engagement positions associated with the plurality of shift lever positions, respectively, the shift lever being coupled to an engagement member, the engagement member moving with the shift lever and being biased to selectively engage a selected one of the plurality of the engagement positions associated with a selected one of the shift lever positions to command the aircraft flaps to the flap position associated with the selected one of the shift lever positions. The shift lever indexing plate includes a web portion which separates the engagement positions of the shift lever indexing plate, the web portion and the shift lever being shaped and the shift lever being biased such that when the shift lever is at rest and only the shift lever bias is applied to the shift lever, the engagement member must be engaged with one of the plurality of engagement positions of the shift lever indexing plate.

    Abstract translation: 一种用于控制飞行器中的襟翼定位的装置，包括可移动到多个换档杆位置中的每一个的变速杆，以控制飞行器的翼片对相应的多个相关翼片位置中的每一个的定位。 变速杆分度板分别包括与多个变速杆位置相关联的多个接合位置，变速杆联接到接合构件，接合构件与变速杆一起移动并被偏置以选择性地接合选定的一个 所述多个接合位置与所述变速杆位置中选择的一个相关联，以指示飞行器将飞翼折回到与所选择的换档杆位置相关联的挡板位置。 变速杆分度板包括腹板部分，其分离变速杆分度板的接合位置，腹板部分和变速杆成形，变速杆被偏压，使得当变速杆处于静止状态时，仅变速杆 偏移被施加到变速杆，接合构件必须与变速杆分度盘的多个接合位置中的一个接合。

    Awareness Enhancing Display For Aircraft
    17.
    发明申请
    Awareness Enhancing Display For Aircraft 有权
    意识增强飞机显示

    公开(公告)号：US20150348420A1

    公开(公告)日：2015-12-03

    申请号：US14643571

    申请日：2015-03-10

    Applicant: Cessna Aircraft Company

    Inventor： Jeremy Joseph Kneuper ,  Isaac Wayne Stanfield ,  Jason Michael Decker

    IPC: G08G5/00 ,  G08G5/04

    CPC classification number: G08G5/0021 ,  B64D43/00 ,  G01C23/00 ,  G01C23/005 ,  G06F3/0481 ,  G06F3/04817 ,  G06F3/04847 ,  G08G5/0052

    Abstract: Systems, methods and computer-storage media are provided for enhancing awareness in an aircraft using a touch-screen instrument panel. In one aspect, a warning is displayed peripherally in the panel in a way that attracts attention without interfering with the use of the panel for other purposes. In another aspect, a crew member is directed by highlighting through menus to a screen that enables the problem causing the warning to be corrected. In another aspect, parameters (e.g., temperatures, pressures) are displayed along with oriented graphical representations of system components. In yet another aspect, aircraft parameters are displayed in a historical context so that the user has a time-line context for a value at issue.

    Abstract translation: 提供了系统，方法和计算机存储介质，以提高使用触摸屏仪表板的飞行器的意识。 在一个方面，警告在面板中以外部的方式显示，以引起注意，而不妨碍面板用于其他目的。 在另一方面，通过将菜单突出显示到屏幕上来引导机组成员，该屏幕使得能够纠正警告的问题。 在另一方面，参数（例如，温度，压力）与系统组件的定向图形表示一起显示。 在另一方面，飞行器参数以历史上下文显示，使得用户具有所讨论的值的时间线上下文。

    System and method for reduced flammability of an aircraft fuel system
    19.
    发明授权
    System and method for reduced flammability of an aircraft fuel system 有权
    降低飞机燃料系统易燃性的系统和方法

    公开(公告)号：US09090356B2

    公开(公告)日：2015-07-28

    申请号：US13966738

    申请日：2013-08-14

    Applicant: Cessna Aircraft Company

    Inventor： Michael Scott Montgomery

    IPC: B64D37/02 ,  B64D37/04 ,  B64D37/12 ,  B64D37/32

    CPC classification number: B64D37/32 ,  B64D37/04

    Abstract: Disclosed is a method for controlling the flammability of fuel vapors in an aircraft main fuel tank that is located in whole or in part in the fuselage contour. The method comprises a fuel system architecture and fuel consumption sequencing maintaining liquid fuel in said main tanks during all normal operations. Ceasing the withdrawal of fuel from the main tank when the fuel reaches a predetermined level thereby limiting the volume and flammability exposure time of the fuel vapor ullage. Once the predetermined level is met the fuel is supplied from wing tanks throughout the remainder of the mission. The predetermined main tank fuel level at which wing tank fuel begins to be consumed is determined by the aircraft flight reserves fuel volume stored in the main tank as well as the amount necessary to continuously submerge the main tank fuel pumps during the entire mission.

    Abstract translation: 公开了一种控制整个或部分位于机身轮廓中的飞行器主燃料箱中的燃料蒸汽的可燃性的方法。 该方法包括在所有正常操作期间在所述主油箱中保持液体燃料的燃料系统结构和燃料消耗顺序。 当燃料达到预定水平时，停止燃油从主油箱的撤出，从而限制燃油蒸汽消耗的体积和可燃性暴露时间。 一旦满足预定水平，燃油就从任务的其余部分的翼舱提供。 机舱油箱燃料开始消耗的预定主油箱燃料油位由存储在主油箱中的飞机储备燃料量以及整个任务期间连续淹没主油箱燃油泵所需的量决定。

    Thermal insulation barrier for an aircraft de-icing heater
    20.
    发明授权
    Thermal insulation barrier for an aircraft de-icing heater 有权
    飞机除冰加热器的隔热屏障

    公开(公告)号：US08998144B2

    公开(公告)日：2015-04-07

    申请号：US13678282

    申请日：2012-11-15

    Applicant: Cessna Aircraft Company

    Inventor： Richard Boone ,  John W. Gallman

    IPC: B64D15/12

    CPC classification number: B64D15/12

    Abstract: A structure for use with an electrothermal heating element is disclosed comprising a heating element contained in a mat and heater supports attached to one surface of the mat. The heating element is disposed between the skin and internal structure of an aircraft with the heater supports disposed toward the internal structure thereof. The heater supports maintain an insulating layer of air between the mat and the internal structure of the aircraft.

    Abstract translation: 公开了一种与电热加热元件一起使用的结构，它包括一个包含在垫中的加热元件和附着在该垫的一个表面上的加热器支架。 加热元件设置在飞行器的皮肤和内部结构之间，其中加热器支撑件朝向其内部结构设置。 加热器支撑件在垫和飞行器的内部结构之间保持绝缘的空气层。

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