公开(公告)号：US09604727B2

公开(公告)日：2017-03-28

申请号：US14713438

申请日：2015-05-15

Applicant: AIRBUS OPERATIONS (S.A.S.)

Inventor： Amaury Delbosc

IPC: B64D27/26 ,  B64C7/02 ,  B64D29/02

CPC classification number: B64D27/26 ,  B64C7/02 ,  B64D29/02

Abstract: An aerodynamic fairing for a pylon of a turbojet engine, the fairing including: a frame oriented in a plane transverse to a longitudinal axis of the pylon, wherein the frame includes an upper edge, opposite side edges and a lower edge; a deck attached to the lower edge of the frame; a downstream portion of the deck includes a front edge region overlapping a rear edge portion of an upstream portion of the deck, wherein an upper surface of the front edge region is joined to the lower edge of the frame such that the front edge portion is sandwiched between the lower edge of the frame and the rear edge region of the upstream portion of the deck, and a flange extends between and attaches the upstream portion of the deck and the frame and a gap is between the lower edge of the frame and the upstream portion of the deck.

公开(公告)号：US09561868B2

公开(公告)日：2017-02-07

申请号：US14586433

申请日：2014-12-30

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

Inventor： Thierry Bourret ,  Kenji Ahualle Horimoto

IPC: B64D45/04 ,  G05D1/06 ,  B64C13/18 ,  G01C23/00 ,  G05D1/04

CPC classification number: B64D45/04 ,  B64C13/18 ,  G01C23/005 ,  G05D1/042 ,  G05D1/0676

Abstract: A method and device including a unit to extract a linear terrain profile stored in memory, a terrain height for a current distance of the aircraft, a unit for determining a current height of the aircraft with respect to the terrain, using at least one measurement taken by a radar altimeter, a unit for computing a first current altitude of the aircraft, using the terrain height and the current height, a unit for computing a second current altitude of the aircraft, corresponding to an altitude on an approach profile of the current position of the aircraft and a unit for computing the difference between the first and second current altitudes, the difference being transmitted to a guidance unit to vertically guide the aircraft.

Abstract translation: 一种包括提取存储在存储器中的线性地形剖面的单元的方法和装置，飞行器当前距离的地形高度，用于使用至少一次测量来确定飞机相对于地形的当前高度的单元 通过雷达高度计，用于使用地形高度和当前高度来计算飞行器的第一当前高度的单元，用于计算飞行器的第二当前高度的单元，其对应于当前位置的接近轮廓上的高度 并且用于计算第一和第二当前高度之间的差异的单元，差异被传送到引导单元以垂直地引导飞行器。

公开(公告)号：US20170028520A1

公开(公告)日：2017-02-02

申请号：US15217438

申请日：2016-07-22

Applicant: AIRBUS OPERATIONS (S.A.S.)

Inventor： Marion JESU PLU ,  Marc LELAY ,  Perig LE HENAFF ,  Giovanni LOIACONO ,  Fabio VASELLI

IPC: B23P19/06 ,  B23Q9/00

CPC classification number: B23P19/06 ,  B23P2700/01 ,  B23Q9/0007 ,  B23Q9/0042 ,  B23Q17/2471 ,  B64F5/10 ,  G05B19/402 ,  G05B2219/45091 ,  G05B2219/49113 ,  Y02P70/585

Abstract: A tool-support system for working on holes of a surface. The tool-support system includes two rails fixed to the surface and having imprints regularly distributed over their length, and a mobile tool-support including a mobile optical system capturing an image of the surface. For each rail, at least one wheel is adapted to be moved on the rail, and includes on its rolling strip counter-imprints complementary to the imprints. A mobile tool carries a working tip, and a control unit is configured to control the movement of the mobile tool-support, of the tool and of the optical system to analyze an image captured by the optical system and to detect the presence of a hole. A tool-support system of this kind can therefore move along the rails without slipping while detecting the holes to work on them.

Abstract translation: 用于在表面孔上工作的工具支撑系统。 工具支撑系统包括固定在表面上的两个导轨，其长度上规则地分布有印记，以及包括捕获表面图像的移动光学系统的移动工具支架。 对于每个轨道，至少一个轮适于在轨道上移动，并且在其滚动条上包括与印记互补的反印迹。 移动工具携带工作尖端，并且控制单元被配置为控制移动工具支撑件，工具和光学系统的移动，以分析由光学系统捕获的图像并检测孔的存在 。 因此，这种工具支撑系统可以沿着轨道移动而不会滑动，同时检测孔以在其上工作。

公开(公告)号：US09550562B2

公开(公告)日：2017-01-24

申请号：US14283290

申请日：2014-05-21

Applicant: Airbus Operations S.A.S.

Inventor： Florian Constans ,  Josep Boada-Bauxell ,  Pierre Scacchi

IPC: B64C13/18 ,  B64C19/00 ,  B64D31/04 ,  B64C13/04 ,  B64C13/16 ,  B64D31/06

CPC classification number: B64C19/00 ,  B64C13/04 ,  B64C13/16 ,  B64D31/04 ,  B64D31/06

Abstract: A system for controlling an aircraft control parameter including a control interface including a mobile element configured to move on a travel, of which at least two portions are separated by a neutral position; a return element bringing the mobile element back to the neutral position when it is not actuated; and an interaction element, and a control unit configured to memorize an item of information corresponding to a first position of the mobile element at an instant of activation of the interaction element; and generate a setpoint of the aircraft control parameter, as a function of a control associated with the first position of the mobile element for which said information has been memorized; or a current position of the mobile element, when this current position is situated on the same portion of travel as the first position and is more remote than the latter from the neutral position.

Abstract translation: 一种用于控制飞行器控制参数的系统，其包括控制接口，所述控制接口包括被配置为在行程上移动的移动元件，其中至少两个部分被中立位置分隔; 返回元件，当移动元件未被启动时返回到中立位置; 以及控制单元，被配置为在所述交互元件的激活时刻存储对应于所述移动元件的第一位置的信息项; 并且根据与已经存储了所述信息的移动元件的第一位置相关联的控制来生成飞行器控制参数的设定点; 或当该当前位置位于与第一位置相同的行进部分上并且比中立位置更远离移动元件的当前位置时，移动元件的当前位置。

公开(公告)号：US20170018125A1

公开(公告)日：2017-01-19

申请号：US15207139

申请日：2016-07-11

Applicant: AIRBUS OPERATIONS (S.A.S.)

Inventor： Sebastien JOVER ,  Jean-Philippe CORBEFIN

IPC: G07C5/08 ,  G07C5/00

CPC classification number: G07C5/085 ,  G07C5/008 ,  G07C5/02 ,  G07C5/08 ,  G07C5/0816 ,  G07C5/0841 ,  G07C2205/02 ,  H04L67/12

Abstract: A system, device and method for recording data in an aircraft including a memory and a network interface through which it is connected to the network. This device is configured for acquiring information from the avionics communication network, and information relative to characteristic events relative to operation of the aircraft, generating indexes corresponding to different times, recording, in a first part of the memory, indexed data corresponding to the information coming from avionics communication network, the indexed data including a set of recordings, each recording corresponding to the combination of information coming from the avionics communication network and an index corresponding to a time associated with that recording; and recording, in a second part of the memory, for several of the characteristic events, information of correspondence between the characteristic event in question and an index corresponding to a time associated with that characteristic event.

Abstract translation: 一种用于在飞行器中记录数据的系统，设备和方法，包括存储器和网络接口，通过该接口连接到网络。 该设备被配置用于从航空电子通信网络获取信息，以及关于相对于飞行器的操作的特征事件的信息，产生与不同时间相对应的索引，在存储器的第一部分中记录对应于信息的索引数据 来自航空电子通信网络的索引数据包括一组记录，每个记录对应于来自航空电子通信网络的信息的组合以及与该记录相关联的时间的索引; 并且在存储器的第二部分中记录几个特征事件，所述特征事件之间的对应关系的信息和与该特征事件相关联的时间对应的索引。

公开(公告)号：US09545992B2

公开(公告)日：2017-01-17

申请号：US14499549

申请日：2014-09-29

Applicant: AIRBUS OPERATIONS S.A.S.

Inventor： Bernard Guering

IPC: B64C3/50 ,  B64C13/24 ,  B64C13/28 ,  B64C13/40 ,  B64C13/50 ,  B64C9/02 ,  B64C9/06 ,  B64C9/16

CPC classification number: B64C3/50 ,  B64C9/02 ,  B64C9/06 ,  B64C9/16 ,  B64C13/24 ,  B64C13/28 ,  B64C13/40 ,  B64C13/50 ,  B64C13/504 ,  Y02T50/32

Abstract: A high-lift trailing edge flap system for an aircraft wing unit is provided. In high-lift trailing edge flap system, the backward movement and the inclination of the trailing edge flap in the extended position are dissociated in order to allow for the incorporation of the actuating mechanism into the wing in the stowed position.

Abstract translation: 提供了一种用于飞机机翼单元的高升力后缘翼片系统。 在高升力后缘翼片系统中，向后移动和后缘翼片处于伸展位置的倾斜被解离，以允许致动机构结合到收起位置的翼中。

公开(公告)号：US20170011638A1

公开(公告)日：2017-01-12

申请号：US15206332

申请日：2016-07-11

Applicant: AIRBUS GROUP INDIA PRIVATE LIMITED ,  AIRBUS (S.A.S.) ,  AIRBUS OPERATIONS (S.A.S.)

Inventor： ASHUTOSH AGRAWAL ,  Georges Myczkowski ,  Brendan Clarke ,  Nicolas Landrin ,  Lucas Babelaere ,  Nathalie Willig ,  Diego Alonso-Tabares

IPC: G08G5/00 ,  G08G5/02

CPC classification number: G08G5/0095 ,  G06Q10/063 ,  G06Q10/0631 ,  G06Q10/06312 ,  G06Q10/06315 ,  G06Q10/06316

Abstract: A system for monitoring scheduled turnaround activities and alerting on time deviation from the scheduled turnaround activities is disclosed. The system includes a ground computing station system, an aircraft on-board system, a cloud, and user interface. The cloud is communicatively coupled to the ground station computing system and the aircraft on-board system. The cloud includes processor and memory. The memory includes an analytics module to obtain actual start and end time stamps associated with scheduled turnaround activities, from touchdown to takeoff of an aircraft, from aircraft on-board systems and a ground station system. The analytics module to determine time deviation of scheduled turnaround activities by analyzing the obtained actual start and end time stamps. The user interface to present each scheduled turnaround activity and determined time deviation of the scheduled turnaround activities.

Abstract translation: 公开了一种用于监视预定的周转活动并提醒与预定的周转活动的时间偏差的系统。 该系统包括地面计算站系统，飞机机载系统，云端和用户接口。 云通信耦合到地面站计算系统和飞机机载系统。 云包括处理器和内存。 内存包括一个分析模块，用于获得与预定的周转活动相关的实际开始和结束时间戳，从触地飞机起飞，飞机机载系统和地面站系统。 分析模块通过分析获得的实际开始和结束时间戳来确定预定周转活动的时间偏差。 用户界面提供每个预定的周转活动并确定预定周转活动的时间偏差。

公开(公告)号：US20160357492A1

公开(公告)日：2016-12-08

申请号：US15167541

申请日：2016-05-27

Applicant: AIRBUS OPERATIONS (S.A.S.)

Inventor： Christine CHARBONNIER ,  Aymeric PERRIN ,  Cedric DESCHEEMAEKER ,  Nicolas ANTONI

IPC: G06F3/14 ,  B64D43/00 ,  G06F3/0481

CPC classification number: G06F3/1423 ,  B64D43/00 ,  G01C23/00 ,  G06F3/0481 ,  G06F2203/04803 ,  G09G5/00 ,  G09G2354/00 ,  G09G2380/12

Abstract: A display system and method including screens in a cockpit of an aircraft. A control unit is configured to command the display according to a normal display mode, wherein the control unit is configured so as to command the display such that subsequent to the occurrence of an event on board the aircraft leading to the display of an interactive element in an interaction window, the control unit commands the display of the interaction window on one of the screens of the screens at least while an action by an operator is required on the interactive element, and a reconfigured display mode, wherein the control unit is configured to command the display, on a second screen including a signaling area, of a display window that is normally displayed on a first screen in the normal display mode, and to command the display of an indicator in the signaling area if the interaction window is not displayed on a screen of the screens when an action by an operator is required on the interactive element.

Abstract translation: 一种显示系统和方法，包括飞机驾驶舱中的屏幕。 控制单元被配置为根据正常显示模式命令显示器，其中控制单元被配置为命令显示器，使得在飞机上发生事件之后，导致显示交互元件 交互窗口，控制单元至少在交互式元件上需要操作者的动作时，在屏幕的一个屏幕上命令交互窗口的显示，以及重新配置的显示模式，其中控制单元被配置为 在通常显示模式下通常在第一屏幕上显示的显示窗口的第二屏幕上显示包括信令区域的显示器，并且如果不显示交互窗口，则命令显示信令区域中的指示符 在交互式元素上需要操作者的动作时，在屏幕的屏幕上。

公开(公告)号：US09500544B2

公开(公告)日：2016-11-22

申请号：US14978711

申请日：2015-12-22

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

Inventor： Patricia Morgue ,  Manuel Paredes ,  Sophie Gourdon ,  Simon Dols

IPC: G01L3/02 ,  G01L5/00 ,  B23P19/06 ,  B25B23/14 ,  F16B31/02 ,  G01L5/24 ,  G01L5/26

CPC classification number: G01L5/0042 ,  B23P19/066 ,  B25B23/14 ,  B25B23/1425 ,  B25B23/1456 ,  B25B23/147 ,  F16B31/02 ,  G01L5/0076 ,  G01L5/24 ,  G01L5/26

Abstract: A process for checking when tightening a threaded fastener that it has been tightened on the complete threads of the fastener. In order to do this the process comprises detecting different gradients in a tightening graph representing torque as a function of another parameter and comparing each gradient with predetermined values. According to the portions of graph detected and their gradient values it is possible to determine whether tightening is correct and has taken place on the complete threads of the fastener, or if not it is possible to identify a cause of failure.

Abstract translation: 在紧固螺纹紧固件时检查其已被紧固在紧固件的整个螺纹上的过程。 为了做到这一点，该过程包括检测表示作为另一个参数的函数的扭矩的紧固图中的不同梯度，并将每个梯度与预定值进行比较。 根据检测到的曲线图及其梯度值，可以确定紧固件的紧固是否正确，并且已经发生在紧固件的整个螺纹上，或者如果不能确定故障原因。

公开(公告)号：US09495878B2

公开(公告)日：2016-11-15

申请号：US14473548

申请日：2014-08-29

Applicant: AIRBUS OPERATIONS (S.A.S.)

Inventor： Boris Kozlow

IPC: G08G5/00 ,  G01C21/20 ,  G05D1/10 ,  G06F11/00

CPC classification number: G08G5/0047 ,  G01C21/20 ,  G05D1/101 ,  G06F11/00 ,  G08G5/0039

Abstract: A method and device are disclosed for automatically managing a flight path change on an aircraft, in particular for a low-level flight. The method determines a first deviation between the current position and a current path of the aircraft and a second deviation between this current position and a new path of the aircraft and changes the flight path by replacing the current path by the new path, if at least the absolute value of the difference between this first deviation and this second deviation is less than or equal to a maximal allowed distance during at least a predefined time period.

Abstract translation: 公开了一种用于自动管理飞行器上的飞行路线变化的方法和装置，特别是用于低级飞行。 该方法确定当前位置和飞行器的当前路径之间的第一偏差以及该当前位置与飞行器的新路径之间的第二偏差，并通过将当前路径替换为新路径来改变飞行路径，如果至少 该第一偏差与该第二偏差之间的差的绝对值小于或等于至少在预定时间段内的最大允许距离。