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401 条记录 (耗时 0.016 秒)

    ROTATION WARNING
    2.
    发明公开
    ROTATION WARNING 审中-公开

    公开(公告)号：US20230166860A1

    公开(公告)日：2023-06-01

    申请号：US18071146

    申请日：2022-11-29

    申请人： Airbus SAS

    发明人： Anmol DHANDHANIA

    IPC分类号： B64D45/00 ,  B64C25/28 ,  G08G5/00

    CPC分类号： B64D45/0005 ,  B64C25/28 ,  G08G5/0017

    摘要： A method of warning of early rotation of an aircraft during takeoff is disclosed. An improvement in aircraft performance and passenger comfort can be realised by monitoring for signs of early rotation and warning the pilot of such. By detecting when rotation has been commanded by the pilot, and the aircraft nose has started to lift off the ground, when the speed of the aircraft is below a threshold, early rotation can be determined and an auditory warning can mitigate the impact of that on aircraft performance.

    MAGNETIC SENSOR WITH BIFILAR WINDINGS
    3.
    发明申请
    MAGNETIC SENSOR WITH BIFILAR WINDINGS 审中-公开

    公开(公告)号：US20190234766A1

    公开(公告)日：2019-08-01

    申请号：US15880771

    申请日：2018-01-26

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： Todd MILLER ,  Mehmet TANJU

    IPC分类号： G01D5/20 ,  B64C11/30 ,  B64D45/00

    CPC分类号： G01D5/2013 ,  B64C11/301 ,  B64D45/0005

    摘要： Herein provided are sensing systems, methods, sensors, and methods of manufacturing a sensor for a rotating element in an engine. A magnetic core having first and second ends is positioned with the first end proximate the rotating element. A permanent magnet is positioned proximate the second end of the magnetic core and is configured for subjecting the magnetic core and the rotating element to a magnetic field. A bifilar winding comprising a first wire and a second wire electrically insulated from one another is wrapped around at least a portion of the magnetic core, the bifilar winding configured to generate a first signal in the first wire and a second signal in the second wire in response to rotation of the rotating element relative to the sensor.

    AERODYNAMIC CONTROL SURFACE MOVEMENT MONITORING SYSTEM FOR AIRCRAFT
    4.
    发明申请
    AERODYNAMIC CONTROL SURFACE MOVEMENT MONITORING SYSTEM FOR AIRCRAFT 审中-公开

    公开(公告)号：US20180273199A1

    公开(公告)日：2018-09-27

    申请号：US15469740

    申请日：2017-03-27

    申请人： Hamilton Sundstrand Corporation

    发明人： Erik Harrington ,  Christian Miller ,  Yuniya S. Bishop

    IPC分类号： B64D45/00 ,  B64C9/18 ,  B64D47/02

    CPC分类号： B64D45/0005 ,  B64C9/16 ,  B64C9/22 ,  B64C13/28 ,  B64D45/00 ,  Y02T50/44

    摘要： Actuator systems and methods for controlling aerodynamic control surfaces of aircraft including a first actuator receiving a first input and a first linear translation element that moves based thereon, the first linear translation element operably connected to a first portion of the control surface. A first sensor assembly is disposed relative to the first actuator that generates an output based on a displacement of the first translation element. A second actuator receives a second input and a second linear translation element moves based on the second input, the second linear translation element operably connected to a second portion of the control surface. A second sensor assembly is disposed relative to the second actuator that generates a second sensor output based on a displacement of the second translation element. A controller generates the inputs and receives the sensor outputs to determine if an error condition exists for the system.

    Remote Optical Control Surface Indication System
    6.
    发明申请
    Remote Optical Control Surface Indication System 审中-公开

    公开(公告)号：US20180201390A1

    公开(公告)日：2018-07-19

    申请号：US15407076

    申请日：2017-01-16

    申请人： The Boeing Company

    发明人： David M. Konyndyk ,  Jerry A. James

    IPC分类号： B64D45/00 ,  B64D47/08 ,  H04N5/33 ,  G08B5/02

    CPC分类号： B64D45/0005 ,  B64D47/08 ,  H04N5/2252 ,  H04N5/2256 ,  H04N5/33

    摘要： A remote optical control surface indication system comprising mechanisms configured to engage heads of respective fasteners that attach an alignment indexing plate to a vehicular structure having a control surface coupled thereto. The system further comprises: a camera having a field of view that encompasses a portion of an end face of the control surface when the mechanisms are engaged with the fasteners and when the control surface is in a neutral position; a source of light that is activatable to project light that illuminates the end face of the control surface; a display screen comprising an array of pixels; and a computing system configured to process image data captured by the camera to determine a current position of a centerline of the end face of the control surface relative to a baseline position and control the display screen to display symbology indicating the current position relative to the baseline position.

    METHOD OF DETECTING ELEVATOR TAB FAILURE
    10.
    发明申请
    METHOD OF DETECTING ELEVATOR TAB FAILURE 审中-公开

    公开(公告)号：US20180082499A1

    公开(公告)日：2018-03-22

    申请号：US15810587

    申请日：2017-11-13

    申请人： UNITED AIRLINES, INC.

    发明人： Paul Bowman ,  Ryan Nurnberger

    IPC分类号： G07C5/08 ,  B64C13/40

    CPC分类号： G07C5/0816 ,  B64C9/10 ,  B64C9/12 ,  B64C13/42 ,  B64D45/00 ,  B64D45/0005

    摘要： A method is provided for verifying proper operation of a left elevator tab disposed at an end portion of a left elevator of an aircraft and a right elevator tab disposed at an end portion of a right elevator of the aircraft. Because proper operation of the elevator tabs cannot be directly verified by existing aircraft instrument, the operation of the elevator tabs can be indirectly verified by analyzing flight data of the aircraft. After identification of a verification event, in which the elevator tabs move relative to the elevators, the positions of the left elevator and right elevator can be measured, and differences in the positions of the left elevator and right elevator can indicate proper operation of the left and right elevator tabs.