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    AIRCRAFT PILOTING ASSISTANCE SYSTEM AND METHOD
    2.
    发明申请
    AIRCRAFT PILOTING ASSISTANCE SYSTEM AND METHOD 审中-公开
    飞机引导辅助系统和方法

    公开(公告)号：US20160272336A1

    公开(公告)日：2016-09-22

    申请号：US15063940

    申请日：2016-03-08

    Applicant: DASSAULT AVIATION

    Inventor： Sébastien LEPAGE

    IPC: B64D31/08

    CPC classification number: G05D1/0066 ,  B64C13/16 ,  B64C19/02 ,  B64D31/08 ,  G01C23/00 ,  G05D1/0055 ,  G05D1/0816

    Abstract: A piloting assistance system for an aircraft during manual piloting is provided. The piloting assistance system includes a monitoring module, configured to compare an acceleration of the aircraft to an authorized acceleration that depends on a speed of the aircraft, an acceleration control module, able to be switched between an activated state and a deactivated state, and configured so as, in the activated state, excluding the deactivated state, to generate a control signal of at least one control device of the acceleration of the aircraft to push the acceleration of the aircraft toward the authorized acceleration range, in order to keep or push the speed of the aircraft in a predefined usage speed range, the monitoring module being configured to activate the acceleration control module when the acceleration of the aircraft is not comprised in the authorized acceleration range.

    Abstract translation: 提供了在手动驾驶期间为飞机提供驾驶辅助系统。 驾驶辅助系统包括监视模块，其被配置为将飞行器的加速度与取决于飞行器速度的授权加速度进行比较，加速控制模块能够在激活状态和停用状态之间切换，并配置 在激活状态下，除了去激活状态之外，为了产生飞行器的加速度的至少一个控制装置的控制信号，将飞行器的加速度推向授权的加速度范围，以便保持或推动 所述监视模块被配置为当所述飞机的加速度不包括在所述授权的加速度范围内时激活所述加速控制模块。

    DISPLAY SYSTEM OF AN AIRCRAFT, COMPRISING A FLARE GUIDING CUE AND RELATED METHOD
    3.
    发明申请
    DISPLAY SYSTEM OF AN AIRCRAFT, COMPRISING A FLARE GUIDING CUE AND RELATED METHOD 审中-公开
    飞行器显示系统，包含一个引导引擎和相关方法

    公开(公告)号：US20160379502A1

    公开(公告)日：2016-12-29

    申请号：US15189907

    申请日：2016-06-22

    Applicant: DASSAULT AVIATION

    Inventor： Sébastien LEPAGE ,  Olivier BAUDSON ,  Arnaud TURPIN

    IPC: G08G5/02 ,  G08G5/00 ,  B64D45/08

    CPC classification number: G08G5/025 ,  B64D43/00 ,  B64D45/08 ,  G01C23/005 ,  G08G5/0021 ,  G08G5/0086

    Abstract: A display system of an aircraft, including a flare guiding cue and related method are provided. The display system includes a display unit; and an assembly for generating a display on the display unit, configured to dynamically display, on the display unit, at least one horizon line, a slope scale of the aircraft relative to the horizon line, and a speed vector symbol, representative of the slope of the aircraft relative to the horizon line. The display generator is configured to display, upon approaching a landing strip, a flare guidance symbol, the position of the flare guidance symbol on the display unit depending on the topographical slope of the approached landing strip.

    Abstract translation: 提供飞机的显示系统，包括火炬指导提示和相关方法。 显示系统包括显示单元; 以及用于在所述显示单元上生成显示器的组件，被配置为在所述显示单元上动态地显示所述飞机相对于所述水平线的至少一个水平线，斜率以及代表所述斜率的速度矢量符号 的飞机相对于地平线。 显示发生器被配置为在接近着陆条时，根据接近的着陆带的地形坡度，在展示单元上显示火炬引导符号的位置。

    METHOD FOR DYNAMICALLY DETERMINING THE POSITION OF THE STOP POINT OF AN AIRCRAFT ON A TERRAIN, AND ASSOCIATED SYSTEM
    4.
    发明申请
    METHOD FOR DYNAMICALLY DETERMINING THE POSITION OF THE STOP POINT OF AN AIRCRAFT ON A TERRAIN, AND ASSOCIATED SYSTEM 有权
    用于动态地确定飞机上的停止点位置的方法和相关系统

    公开(公告)号：US20140148980A1

    公开(公告)日：2014-05-29

    申请号：US14089535

    申请日：2013-11-25

    Applicant: DASSAULT AVIATION

    Inventor： Nicolas LE CORRE ,  Sébastien LEPAGE ,  Alain BOUCHER

    IPC: G08G5/00

    CPC classification number: G08G5/00 ,  G05D1/0083 ,  G05D1/0676 ,  G08G5/025

    Abstract: The method according to the invention comprise the following steps, dynamic measurement of the current geographical position of the aircraft, and its current ground speed, calculation of a first length representative of a flight phase of the aircraft, and calculation of a second length representative of a ground phase of the aircraft, calculation of the position of the stop point based on the first length, the second length and the current geographical position. The calculation of the first length comprises a phase for dynamically estimating a distance traveled by the aircraft during at least part of a flare phase of the aircraft.

    Abstract translation: 根据本发明的方法包括以下步骤：飞行器当前地理位置的动态测量及其当前地面速度，代表飞行器飞行阶段的第一长度的计算，以及代表飞行器的第二长度的计算 飞机的地面相位，基于第一长度，第二长度和当前地理位置计算停止点的位置。 第一长度的计算包括一个阶段，用于动态地估计飞机在至少部分飞机的火炬阶段期间行驶的距离。

    DEVICE FOR DISPLAYING AN ENERGY VARIATION AND AN ENERGY VARIATION BOUND OF AN AIRCRAFT
    6.
    发明申请
    DEVICE FOR DISPLAYING AN ENERGY VARIATION AND AN ENERGY VARIATION BOUND OF AN AIRCRAFT 审中-公开
    用于显示能量变化和飞机能量变化的装置

    公开(公告)号：US20160274739A1

    公开(公告)日：2016-09-22

    申请号：US15064502

    申请日：2016-03-08

    Applicant: DASSAULT AVIATION

    Inventor： Sébastien LEPAGE ,  Hasna NADFAOUI

    IPC: G06F3/0481 ,  B64D43/00 ,  G01C23/00

    CPC classification number: G06F3/0481 ,  B64D43/00 ,  G01C23/00 ,  G01C23/005

    Abstract: A display device for displaying information relative to a flight by an aircraft is provided. The information includes information relative to an energy variation of the aircraft, the energy variation being expressed by a variable representative of that energy variation. The display device is configured to show, on a viewing screen, an energy variation symbol representative of a current value of the variable. The display device is configured to further show at least one energy variation bound symbol representative of a threshold value of the variable, the threshold value corresponding to an authorized acceleration bound for the aircraft to keep or bring the speed of the aircraft in or toward a predefined usage speed range.

    Abstract translation: 提供了一种用于通过飞行器显示关于飞行的信息的显示装置。 信息包括相对于飞行器的能量变化的信息，能量变化由表示该能量变化的变量表示。 显示装置被配置为在观看屏幕上显示表示变量的当前值的能量变化符号。 显示装置被配置为进一步显示表示变量的阈值的至少一个能量变化绑定符号，该阈值对应于飞行器保持或使飞行器的速度保持在或朝向预定义的速度的授权加速度 使用速度范围。

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