公开(公告)号：US20150017915A1

公开(公告)日：2015-01-15

申请号：US14155194

申请日：2014-01-14

Applicant: DASSAULT AVIATION

Inventor： Arnaud HENNEQUIN ,  Hugues ABRASSART

IPC: G08C17/02 ,  H04B1/38 ,  H04W4/00

CPC classification number: G08C17/02 ,  H04B1/3822 ,  H04B7/18506 ,  H04N21/214 ,  H04W4/80

Abstract: The system according to the invention comprises a mobile electronic device, at least one local base, arranged near a predefined location in the cabin, an assembly for pairing the mobile electronic device with the local base, and at least one piece of functional equipment for managing the cabin environment. The memory of the mobile electronic device stores at least one software application for controlling the functional equipment. The pairing system is capable of sending the mobile electronic device at least one location identification data of the local base during pairing between the mobile electronic device and the local base, the mobile electronic device being able to configure the control software application, based on the location identification data.

Abstract translation: 根据本发明的系统包括移动电子设备，布置在机舱内的预定位置附近的至少一个本地基座，用于将移动电子设备与本地基座配对的组件以及用于管理的至少一个功能设备 客舱环境。 移动电子设备的存储器存储用于控制功能设备的至少一个软件应用程序。 配对系统能够在移动电子设备和本地基站之间配对期间向移动电子设备发送本地基站的至少一个位置标识数据，移动电子设备能够基于位置来配置控制软件应用 识别数据。

公开(公告)号：US20140207314A1

公开(公告)日：2014-07-24

申请号：US13851667

申请日：2013-03-27

Applicant: DASSAULT AVIATION

Inventor： Paul KOU ,  Jerome BARRAL ,  Cyril SAINT-REQUIER ,  Eric BOULLE

IPC: B64D45/00

CPC classification number: B64D45/00 ,  B64D43/00 ,  G01C23/00

Abstract: The system includes additional display means including at least one additional screen and additional graphic interface handling means of the additional screen (able to display on the additional screen, a summary window depending on the operational state of the aircraft. The summary window comprises at least one first pictogram able to be displayed on a first display window of main display means of the aircraft without being displayed on the second window of the main display means, and at least one second pictogram intended to be displayed on the second display window of the main display means without being displayed on the first window of the main display means.

Abstract translation: 该系统包括附加显示装置，其包括附加屏幕的至少一个附加屏幕和附加图形界面处理装置（能够在附加屏幕上显示取决于飞行器的操作状态的汇总窗口），总结窗口包括至少一个 可以在主显示装置的第二窗口上显示的第一个象形图能够显示在主显示装置的主显示装置的第一显示窗口上，以及要显示在主显示器的第二显示窗口上的至少一个第二象形图 意味着不显示在主显示装置的第一窗口上。

公开(公告)号：US20140190765A1

公开(公告)日：2014-07-10

申请号：US14148520

申请日：2014-01-06

Applicant: DASSAULT AVIATION

Inventor： Sébastien BARRÉ

IPC: B64C1/40

CPC classification number: B64C1/40 ,  B64D13/00 ,  B64D41/00 ,  B64D2033/0206 ,  F04B39/0055 ,  F04B49/06 ,  F16L55/02763 ,  F16L55/0336

Abstract: The invention relates to a device for reducing the noise emitted by a conduit belonging to an aircraft system that comprises an acoustic grid positioned in a segment of the conduit. Said grid has a length L1, along the axis (X-X) of said segment, and includes multiple meshes, each of which fits into a square with side m, the following relationships being satisfied: L1>1.8λfmin, m

Abstract translation: 本发明涉及一种用于减少由属于飞行器系统的导管发出的噪声的装置，该装置包括位于导管段中的声栅格。 所述栅格沿着所述段的轴线（XX）具有长度L1，并且包括多个网格，每个网格适合具有边m的正方形，满足以下关系：L1>1.8λfmin，m <λfmax/ 2， 其中fmax是要衰减的噪声的最大频率，fmin是要衰减的最佳频率，λfmax是频率fmax处噪声的波长，λfmin是频率fmin处噪声的波长。 适用于飞机系统的进出气管道。

公开(公告)号：US20140100721A1

公开(公告)日：2014-04-10

申请号：US14044245

申请日：2013-10-02

Applicant: DASSAULT AVIATION

Inventor： Olivier BAUDSON ,  Arnaud TURPIN

IPC: B64D45/00

CPC classification number: B64D45/00 ,  G01C23/00 ,  G06T19/006

Abstract: The vision system for an aircraft according to the invention comprises a display management system, on a display, capable of dynamically displaying synthetic information coming from a synthetic environment generating assembly on the display. The management assembly can control the display, on a first region of the display, of relief lines representative of the terrain situated facing the aircraft, without displaying synthetic surface representations of the terrain in the intermediate areas situated between the relief lines of the first region of the display. The generating assembly includes means for determining the position of the crest lines of the terrain from topographical data present in at least one database, and means for computing the position of the relief lines from the position of the crest lines of the terrain.

Abstract translation: 根据本发明的用于飞机的视觉系统包括在显示器上能够动态地显示来自合成环境生成组件的合成信息的显示管理系统。 管理组件可以在显示器的第一区域上控制表示面向飞行器的地形的浮雕线的显示，而不在位于第一区域的浮雕线之间的中间区域中的地形的合成表面表示 显示器。 生成组件包括用于根据存在于至少一个数据库中的地形数据确定地形的顶部线的位置的装置，以及用于从地形的顶部线的位置计算浮雕线的位置的装置。

公开(公告)号：US20140062880A1

公开(公告)日：2014-03-06

申请号：US14017459

申请日：2013-09-04

Applicant: DASSAULT AVIATION

Inventor： Cyril SAINT-REQUIER ,  Audren KERVELLA

IPC: G06F3/01

CPC classification number: G06F3/013 ,  B64D43/00 ,  G06F3/012 ,  G06F3/03549 ,  G06F3/04812 ,  G06F3/147 ,  G09G2380/12

Abstract: A system for controlling the position of a movable object on a viewing device in an aircraft cockpit, which can be actuated by an operator includes means for determining, at least at one given moment, a position of a target zone on said viewing device toward which the operator's gaze is directed, and positioning means adapted for placing the object on the target zone of the viewing device.

Abstract translation: 用于控制飞行器驾驶舱中的可视物体在观察装置上的位置的系统，其可由操作者致动器包括用于至少在给定时刻确定所述观察装置上的目标区域的位置的装置， 指示操作者的注视，并且适于将对象放置在观察装置的目标区域上的定位装置。

公开(公告)号：US08527173B2

公开(公告)日：2013-09-03

申请号：US13070402

申请日：2011-03-23

Applicant: Jean-Patrick Lacoste ,  Jean-Jacques Boubal ,  Sébastien Dupont De Dinechin

Inventor： Jean-Patrick Lacoste ,  Jean-Jacques Boubal ,  Sébastien Dupont De Dinechin

IPC: B64C13/18

CPC classification number: G05D1/063

Abstract: The method for managing an energy variation of an aircraft provided with at least one propulsion system, capable of generating a thrust force on said aircraft comprised in a thrust range, is characterized in that said energy variation is expressed by a size representative of said energy variation and homogenous to a gradient of the aircraft, and in that it includes steps for determining the current energy variation of said aircraft, ordering an energy variation of the aircraft, determining, as a function of said ordered energy variation, a necessary thrust force that must be generated by said propulsion system for the energy variation of the aircraft to be able to tend towards said ordered energy variation, and developing and applying a control order to said propulsion system so that it delivers said necessary thrust force.

Abstract translation: 用于管理具有能够在推力范围内包括在所述飞行器上的推力的至少一个推进系统的飞行器的能量变化的方法的特征在于，所述能量变化由表示所述能量变化的尺寸 并且与飞行器的梯度同质化，并且其包括用于确定所述飞行器的当前能量变化的步骤，对飞行器的能量变化进行排序，根据所述有序能量变化确定必要的推力 由所述推进系统产生用于飞机的能量变化以能够趋向所述有序能量变化，并且向所述推进系统开发和应用控制命令，以便其传递所述必要的推力。

公开(公告)号：US20130087238A1

公开(公告)日：2013-04-11

申请号：US13645991

申请日：2012-10-05

Applicant: DASSAULT AVIATION

Inventor： Paul-Andre MERCIER

IPC: F16L11/00 ,  B23Q17/00

CPC classification number: F16L9/18 ,  B64D37/10 ,  B64D37/32 ,  F16L3/26 ,  F16L7/00 ,  Y10T29/4978

Abstract: The pipe (1) according to the invention includes: a fluid circulation hose (3), an outer protective tube (5), arranged around said hose (3) coaxially to said hose (3), and means (9) for centering said hose (3) in the outer protective tube (5). Said outer protective tube (5) comprises: at least one shell (21) in the form of a hollow tube having a transverse section larger than the transverse section of said hose (3), and forming an annular space (7) between said hollow tube and said hose (3) to receive said centering means (9), and an enclosure (23) that is wound on the outer surface of said shell (21), the enclosure (23) sealably surrounding the annular space (7).

Abstract translation: 根据本发明的管道（1）包括：流体循环软管（3），与所述软管（3）同轴布置在所述软管（3）周围的外部保护管（5），以及用于使所述 软管（3）在外保护管（5）中。 所述外保护管（5）包括：具有大于所述软管（3）的横截面的横截面的中空管形式的至少一个壳（21），并且在所述中空管之间形成环形空间（7） 管和所述软管（3）以容纳所述定心装置（9），以及围绕所述壳体（21）的外表面上的外壳（23），所述外壳（23）可密封地围绕所述环形空间（7）。

公开(公告)号：US20120291426A1

公开(公告)日：2012-11-22

申请号：US13471801

申请日：2012-05-15

Applicant: Renaud LOISON

Inventor： Renaud LOISON

IPC: F02C6/00 ,  F02C1/02 ,  F02C3/04

CPC classification number: B64D13/06 ,  B64D41/00 ,  B64D2013/0644 ,  B64D2241/00 ,  Y02E20/14 ,  Y02T50/44 ,  Y02T50/56

Abstract: The system according to the invention comprises a rotary shaft (50), a compressor (54) mounted integral with the rotary shaft (50), a power turbine (52) capable of rotating the rotary shaft (50), a cold expansion turbine (56) rotated by the rotary shaft (50) and supplied with a compressed gas from the compressor (54) toward the cold turbine (56).The system (22) comprises an upstream assembly (42) supplying outside air to the aircraft not having passed through a propulsion engine (16A, 16B) of the aircraft, the upstream supply assembly (42) being connected to an inlet of the compressor (54).

Abstract translation: 根据本发明的系统包括旋转轴（50），与旋转轴（50）整体安装的压缩机（54），能够旋转旋转轴（50）的动力涡轮机（52），冷膨胀涡轮机 56）由旋转轴（50）旋转，并从压缩机（54）向冷却涡轮（56）供给压缩气体。 该系统（22）包括一个上游组件（42），该外部组件（42）向没有通过飞行器的推进发动机（16A，16B）的飞机提供外部空气，上游供应组件（42）连接到压缩机的入口 54）。

公开(公告)号：US6088923A

公开(公告)日：2000-07-18

申请号：US46651

申请日：1998-03-24

Applicant: Sylvain Guerin

Inventor： Sylvain Guerin

IPC: G01B5/20 ,  G01B11/03 ,  G01B11/24 ,  G01B3/00

CPC classification number: G01B5/201 ,  G01B11/2408

Abstract: A sensor arm (1) is inserted into a hole (3). The arm is mounted on a pivot (5) perpendicular to the arm axis so that it may be urged into engagement with the wall of the hole, e.g. by an air cylinder (12). The pivot (5) is in turn rotated about an axis passing through the hole, preferably by means of a rotary body (10). A bearing piece (16) controlling the sensor arm may be moved towards or away from the hole and rigidly supports a light sensor (8) that receives a light beam (7) from the sensor arm. The geometry of the hole is determined on the basis of the position where the light beam impinges on the sensor and the position of the bearing piece relative to the hole.

Abstract translation: 传感器臂（1）插入孔（3）中。 臂安装在垂直于臂轴线的枢轴（5）上，使得其可被推动与孔的壁接合，例如， 通过气缸（12）。 枢轴（5）又绕通过孔的轴旋转，优选通过旋转体（10）旋转。 控制传感器臂的轴承件（16）可朝向或远离孔移动，并刚性地支撑从传感器臂接纳光束（7）的光传感器（8）。 孔的几何形状基于光束照射在传感器上的位置和轴承片相对于孔的位置而确定。

公开(公告)号：US6038498A

公开(公告)日：2000-03-14

申请号：US950974

申请日：1997-10-15

Applicant: Michel Briffe ,  Guy Mitaux-Maurouard

Inventor： Michel Briffe ,  Guy Mitaux-Maurouard

IPC: G01C23/00 ,  G06F17/00

CPC classification number: G01C23/00

Abstract: An aircraft includes a system for managing check lists solely by operation of a four-position rocker switch having a center return position. The system includes check list data organized into three levels and automatically displayed upon occurrence of an abnormal condition.

Abstract translation: 飞机包括仅通过操作具有中心返回位置的四位置摇摆开关来管理检查表的系统。 该系统包括组织成三级的检查表数据，并且在出现异常状况时自动显示。