中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

11 records (took 0.015 seconds)

    Apparatus and method for maintaining a tension in a cable control system
    1.
    发明授权
    Apparatus and method for maintaining a tension in a cable control system 有权
    用于维持电缆控制系统中的张力的装置和方法

    公开(公告)号：US09359066B2

    公开(公告)日：2016-06-07

    申请号：US14117793

    申请日：2011-05-19

    Applicant: Harris Butler

    Inventor： Harris Butler

    IPC: B64C13/30 ,  F16C1/22

    CPC classification number: B64C13/30 ,  F16C1/22

    Abstract: A cable support apparatus for an aircraft cable control system comprises at least one cable support unit. The cable support unit includes a pulley adapted to carry a cable of the aircraft cable control system, a support link with a first joint between the pulley and the support link and a second joint between the support link and the structure of the aircraft, and a compensation link connected with the structure of the aircraft. The thermal expansion of the compensation link causes a displacement of the support link. An aircraft and a method for maintaining a tension of a cable of a cable control system of an aircraft are also provided.

    Abstract translation: 一种用于飞机电缆控制系统的电缆支撑装置包括至少一个电缆支撑单元。 电缆支撑单元包括适于承载飞行器电缆控制系统的电缆的滑轮，具有在滑轮和支撑连杆之间的第一接头的支撑连杆以及支撑连杆和飞行器的结构之间的第二接头，以及 补偿链接与飞机结构相连。 补偿连杆的热膨胀导致支撑连杆的位移。 还提供了一种用于维持飞机的电缆控制系统的电缆的张力的飞机和方法。

    Optical viewing apparatus for aircraft doorway
    2.
    发明授权
    Optical viewing apparatus for aircraft doorway 有权

    公开(公告)号：US10252818B2

    公开(公告)日：2019-04-09

    申请号：US14441413

    申请日：2013-11-14

    Applicant: LEARJET INC. ,  Harris K. Butler, III ,  Kris Rustman

    Inventor： Harris K. Butler, III ,  Kris Rustman

    IPC: H04N7/18 ,  B64D47/08 ,  B64C1/14 ,  B64D45/00 ,  G02B23/08 ,  H04N7/20 ,  G02B6/06

    Abstract: A viewing device for an aircraft includes an image receiver adapted to receive an image of a predetermined spatial area of an exterior of an aircraft, an image projector adapted to display the image of the predetermined spatial area, and an image conduit connecting the image receiver to the image projector. The image receiver is adapted to be positioned on an exterior side of the aircraft below a lateral width of a fuselage of the aircraft while the image projector is adapted to be positioned on an interior side of the aircraft above the lateral width of the fuselage of the aircraft. The image projector is adapted to be positioned at a first predetermined height above a floor on the interior side of the aircraft, consistent with a person's eye level. The image projector is separated from the image receiver by a first predetermined distance.

    Composite material incorporating water ingress barrier
    4.
    发明授权
    Composite material incorporating water ingress barrier 有权

    公开(公告)号：US10220593B2

    公开(公告)日：2019-03-05

    申请号：US14907317

    申请日：2014-07-01

    Applicant: LEARJET INC.

    Inventor： Khassan Mourtazov ,  Pierre Drolet ,  Pierre Harter ,  David Wilson

    IPC: B32B3/12 ,  B29D99/00 ,  B32B37/14 ,  B32B37/12 ,  B32B5/02 ,  B32B5/26 ,  B32B7/10 ,  B32B7/12 ,  B32B38/00

    Abstract: A composite material includes a honeycomb layer with top and bottom sides. The honeycomb layer includes a plurality of walls defining a plurality of cells therein. A first adhesive layer is disposed adjacent to the top side of the honeycomb layer. A second adhesive layer is disposed adjacent to the bottom side of the honeycomb layer. A third adhesive layer is disposed adjacent to the first adhesive layer on the top side of the honeycomb layer. A first composite layer is disposed adjacent to the third adhesive layer on the top side of the honeycomb layer. A second composite layer is disposed adjacent to the second adhesive layer on the bottom side of the honey comb layer. At least the third adhesive layer comprises viscous properties that discourage the creation of channels within the first composite layer when co-cured.

    Rudder bias gain changer
    5.
    发明授权
    Rudder bias gain changer 有权
    方向舵偏置增益变换器

    公开(公告)号：US09561846B2

    公开(公告)日：2017-02-07

    申请号：US14232408

    申请日：2011-07-26

    Applicant: Harris K. Butler, III ,  Mihalis Veletas

    Inventor： Harris K. Butler, III ,  Mihalis Veletas

    IPC: B64C13/24 ,  B64C13/28 ,  B64C13/26 ,  B64C13/40

    CPC classification number: B64C13/28 ,  B64C13/24 ,  B64C13/26 ,  B64C13/40

    Abstract: A bias gain system for aircraft rudder comprises a pair of connector ends receiving an actuation force from a bias actuator. A rudder bar interface is positioned between the connector ends. The interface rotates about the rudder bar as a function of the actuation forces from the bias actuators. A mechanism comprises links and joints between the connector ends and the rudder bar is actuatable between a contracted configuration, in which first moment arms are defined between the connector ends and the rudder bar interface, and an expanded gain configuration, in which second moment arms have a greater dimension than the first moment arms. An actuator is connected to the mechanism to actuate the mechanism to actuate the mechanism independently from the actuation forces from the bias actuators, to move the mechanism between configurations. An aircraft and a method for controlling a torque on a rudder bar of an aircraft are also provided.

    Abstract translation: 用于飞机舵的偏置增益系统包括一对连接器端，其接收来自偏压致动器的致动力。 舵杆接口位于连接器端之间。 界面围绕舵杆旋转，作为来自偏压致动器的致动力的函数。 一种机构包括在连接器端部之间的连杆和接头，并且舵杆可在收缩构型之间致动，收缩构型在连接器端部和舵杆接口之间限定了第一时刻臂，以及膨胀增益构造，其中第二力矩臂具有 比第一时刻武器更大的尺寸。 致动器连接到机构以致动机构，以独立于来自偏压致动器的致动力致动机构，以在构造之间移动机构。 还提供了一种用于控制飞机舵杆上的扭矩的飞机和方法。

    RUDDER BIAS GAIN CHANGER
    6.
    发明申请
    RUDDER BIAS GAIN CHANGER 有权

    公开(公告)号：US20140145029A1

    公开(公告)日：2014-05-29

    申请号：US14232408

    申请日：2011-07-26

    Applicant: Harris K. Butler, III ,  Mihalis Veletas

    Inventor： Harris K. Butler, III ,  Mihalis Veletas

    IPC: B64C13/28

    CPC classification number: B64C13/28 ,  B64C13/24 ,  B64C13/26 ,  B64C13/40

    Abstract: A bias gain system for aircraft rudder comprises a pair of connector ends receiving an actuation force from a bias actuator. A rudder bar interface is positioned between the connector ends. The interface rotates about the rudder bar as a function of the actuation forces from the bias actuators. A mechanism comprises links and joints between the connector ends and the rudder bar is actuatable between a contracted configuration, in which first moment arms are defined between the connector ends and the rudder bar interface, and an expanded gain configuration, in which second moment arms have a greater dimension than the first moment arms. An actuator is connected to the mechanism to actuate the mechanism to actuate the mechanism independently from the actuation forces from the bias actuators, to move the mechanism between configurations. An aircraft and a method for controlling a torque on a rudder bar of an aircraft are also provided.

    Abstract translation: 用于飞机舵的偏置增益系统包括一对连接器端，其接收来自偏压致动器的致动力。 舵杆接口位于连接器端之间。 界面围绕舵杆旋转，作为来自偏压致动器的致动力的函数。 一种机构包括在连接器端部之间的连杆和接头，并且舵杆可在收缩构型之间致动，收缩构型在连接器端部和舵杆接口之间限定了第一时刻臂，以及膨胀增益构型，其中第二时刻臂具有 比第一时刻武器更大的尺寸。 致动器连接到机构以致动机构，以独立于来自偏压致动器的致动力致动机构，以在构造之间移动机构。 还提供了一种用于控制飞机舵杆上的扭矩的飞机和方法。

    Methods and apparatus for diagnostics of aircraft and other mobile platforms
    7.
    发明授权
    Methods and apparatus for diagnostics of aircraft and other mobile platforms 有权

    公开(公告)号：US10515491B2

    公开(公告)日：2019-12-24

    申请号：US15510359

    申请日：2015-09-09

    Applicant: LEARJET INC.

    Inventor： Peter Fleming Levy

    IPC: G07C5/12 ,  G07C5/08 ,  G06Q10/00 ,  G06Q10/06 ,  B64D45/00 ,  G07C5/00 ,  G05B19/042 ,  G06F11/32 ,  G06F11/30

    Abstract: Methods and apparatus disclosed herein may facilitate the evaluation of time-correlated operational data associated with a mobile platform more effectively by presenting the relevant data in ways that are relatively straightforward to interpret and more favorable to the identification of potential root causes. In some aspects, the methods and apparatus disclosed herein may facilitate the evaluation of multiple systems simultaneously at different points in time to study the initiation and evolution of one or more faults across one or more systems. In various embodiments, the methods and apparatus disclosed herein make use of graphic user interfaces containing synchronized elements such as two-dimensional plots, fault timelines, alert timelines and status information to facilitate diagnostics of mobile platforms.

    Door for an aircraft
    8.
    发明授权
    Door for an aircraft 有权

    公开(公告)号：US09981732B2

    公开(公告)日：2018-05-29

    申请号：US14900973

    申请日：2014-07-11

    Applicant: LEARJET INC. ,  C&D ZODIAC INC.

    Inventor： William A. Goings ,  Eric Long

    IPC: B64C1/14 ,  B64D11/00 ,  B64D11/02 ,  E05F11/54

    CPC classification number: B64C1/14 ,  B64D11/0023 ,  B64D11/02 ,  E05F11/54 ,  E05Y2900/502

    Abstract: A door for an aircraft includes a first panel divisible into at least two first slats that are releasably connected to one another, a first tensioning cable attached between the at least two first slats, and a first tensioner connected to the first tensioning cable and being operative to apply a first tension thereto, thereby permitting the first tensioning cable to hold the at least two first slats together to form the first panel and to release the first tension in the first tensioning cable upon occurrence of a release action, thereby permitting the at least two first slats to dissociate from one another so that the first panel fragments.

    Tailplane with positive camber
    9.
    发明授权
    Tailplane with positive camber 有权

    公开(公告)号：US09873503B2

    公开(公告)日：2018-01-23

    申请号：US14906605

    申请日：2014-07-21

    Applicant: LEARJET INC.

    Inventor： Reuben Chandrasekharan ,  Nick Iarocci ,  Shermineh Vafa ,  Iyad Akel

    IPC: B64C5/02 ,  B64C9/00

    CPC classification number: B64C5/02 ,  B64C9/00

    Abstract: Tailplanes and empennages for aircraft are disclosed. An exemplary tailplane disclosed includes a stabilizer having a fixed shape and an elevator movably secured to the stabilizer. The elevator is movable from a neutral position relative to the stabilizer. The stabilizer and the elevator define an airfoil cross-sectional shape having a positive camber when the elevator is in the neutral position. The positive camber of the airfoil cross-sectional shape may facilitate movement of the elevator during some flight conditions. Also disclosed are tailplanes having camber distributions that vary along the spans of the tailplanes.

Patent Agency Ranking