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    Method And System For Estimating The Flaps Position Of An Aircraft
    83.
    发明申请
    Method And System For Estimating The Flaps Position Of An Aircraft 审中-公开

    公开(公告)号：US20190162746A1

    公开(公告)日：2019-05-30

    申请号：US16188764

    申请日：2018-11-13

    Applicant: Airbus Operations S.A.S.

    Inventor： David Andissac ,  Maxime Semat

    IPC: G01P13/02

    Abstract: An estimation system includes a module for measuring a current angle of attack and current flight parameters of the aircraft, a module for estimating a current lift coefficient of the aircraft from the current flight parameters and from a mass of the aircraft, a module for estimating an angle of attack for a zero lift from the current angle of attack, from the current lift coefficient and from a slope of an affine part of at least one theoretical curve describing a lift coefficient of the aircraft as a function of an angle of attack, a module for estimating the current position of the flaps of the aircraft from the angle of attack for a zero lift and a module for sending the current position of the flaps to a user device.

    ELECTRICAL LINK COMPRISING AN ELECTRICAL PROTECTION DEVICE
    86.
    发明申请
    ELECTRICAL LINK COMPRISING AN ELECTRICAL PROTECTION DEVICE 审中-公开

    公开(公告)号：US20190148928A1

    公开(公告)日：2019-05-16

    申请号：US16186109

    申请日：2018-11-09

    Applicant: Airbus Operations (S.A.S.)

    Inventor： Patrick OMS

    IPC: H02H1/00 ,  G01R31/02 ,  H02H3/093 ,  G01R31/00

    Abstract: An electrical link includes an electrical protection device. The electrical link, for linking an AC high-voltage generator to a user apparatus, includes an electrical conductor surrounded by a first inner insulating envelope. An electrical protection device includes a conductive sheath around the inner insulating envelope. A fixed DC current generator is connected to a current injection point of the conductive sheath. A circuit breaker that can be activated is on the electrical conductor and configured to break the electrical link when it is activated. A detection module is connected to a current tap-off point of the conductive sheath and to the circuit breaker, the detection module being configured to detect a break in the conductive sheath, a current leak out of the electrical conductor or a current leak out of the sheath and to activate the circuit breaker.

    METHOD OF SYNTHETIC VISUALIZATION OF A SCENE VIEWED FROM AN AIRCRAFT AND TO A SYNTHETIC VISION SYSTEM FOR IMPLEMENTING SUCH A METHOD
    88.
    发明申请
    METHOD OF SYNTHETIC VISUALIZATION OF A SCENE VIEWED FROM AN AIRCRAFT AND TO A SYNTHETIC VISION SYSTEM FOR IMPLEMENTING SUCH A METHOD 审中-公开

    公开(公告)号：US20190114928A1

    公开(公告)日：2019-04-18

    申请号：US16158614

    申请日：2018-10-12

    Applicant: Airbus Operations (S.A.S.)

    Inventor： Thibault Pinchon ,  Fabrice Bousquet

    IPC: G08G5/00 ,  G01C23/00

    Abstract: A method of synthetic visualization of a scene viewed from an aircraft and synthetic vision system. The system includes a processing unit for generating a synthetic image of a scene ahead of the aircraft, a unit for displaying on a visualization screen a background image corresponding to this synthetic image and symbols for piloting the aircraft, and a monitoring device including a unit for generating at least two virtual control elements, representations of the control elements integrated into the synthetic image, a unit for detecting on the synthetic image the representations and their position, and a unit for verifying whether these positions are consistent with position of a line of zero pitch and/or of a line of zero roll of the aircraft, the display being carried out only in case of consistency between these positions, that is to say the absence of any problem of orientation of the synthetic image.

    Assembly for the flight management of an aircraft and method for monitoring guidance instructions for such an assembly
    89.
    发明授权
    Assembly for the flight management of an aircraft and method for monitoring guidance instructions for such an assembly 有权

    公开(公告)号：US10261510B2

    公开(公告)日：2019-04-16

    申请号：US15781932

    申请日：2016-11-24

    Applicant: Airbus Operations S.A.S.

    Inventor： Sylvain Raynaud ,  Jean-Claude Mere ,  Simon Sellem

    IPC: G05D1/00 ,  G01C23/00 ,  B64C13/00 ,  B64C13/18 ,  G08G5/00 ,  G05D1/10

    Abstract: The invention relates to a flight management assembly (1) comprising two guidance chains (2A, 2B), each one provided with a flight management system (3A, 3B), each of said flight management systems (3A, 3B) carrying out at least one calculation of guidance instructions for the aircraft, the flight management assembly (1) also comprising at least one monitoring unit (4A, 4B) designed to monitor the guidance instructions calculated by the two flight management systems (3A, 3B) in such a way as to be able to detect and identify a defective flight management system, the monitoring unit (4A, 4B) comprising a monitoring device (5) which verifies particularly whether the following three conditions are met: a first derivative of extrapolated cross tracks is positive; a second derivative of extrapolated cross tracks is positive; and extrapolated positions of the aircraft are on the same side of an active segment of the flight plan followed by the aircraft as the current position of the aircraft.

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