公开(公告)号：US20170291691A1

公开(公告)日：2017-10-12

申请号：US15484616

申请日：2017-04-11

Applicant: DASSAULT AVIATION

Inventor： Jérôme BARRAL ,  Patrick DARSES

IPC: B64C13/18 ,  B64D43/02 ,  G05D1/10

CPC classification number: B64C13/18 ,  B64D43/02 ,  B64D45/00 ,  G01C23/00 ,  G05D1/101 ,  G08G5/003

Abstract: An assistance method for assisting flying of an aircraft with restriction of possibilities of adjusting the flying parameters depending on the context, and corresponding device are provided. The assistance method for assisting flying of an aircraft includes the steps of: configuring at least one flying mode, the configuration comprising selecting a flying mode selected from among an available flying mode and entering at least one flying setpoint associated with the selected flying mode, presenting the or each configured flying mode, engaging at least one configured flying mode, and flying of the aircraft by an automatic pilot system of the aircraft based on the flying setpoint of the or each engaged flying mode. The method also includes a step for collecting at least one avionics parameter representative of a flying context, and a step for restricting configuration possibilities of the flying modes based on the or each collected avionics parameter.

公开(公告)号：US20170217602A1

公开(公告)日：2017-08-03

申请号：US15418705

申请日：2017-01-28

Applicant: DASSAULT AVIATION

Inventor： Rémi BREBAN

IPC: B64D45/00

CPC classification number: B64D45/00 ,  G05B23/0272

Abstract: A system for assisting in a dispatch decision of an aircraft and related process are provided. The system includes a synthesis module, configured to generate at least one dispatch status for the aircraft, based on at least one defect and/or fault datum of the aircraft received from the acquisition module and at least data contained in a first database and in a second minimum equipment list database; and a display, configured to display at least one synthesis window containing at least one defect and/or fault identification indicator of the aircraft developed from the or each defect and/or fault datum, and at least one dispatch status indicator based on the dispatch status determined by the synthesis module.

公开(公告)号：US09574901B2

公开(公告)日：2017-02-21

申请号：US14388770

申请日：2013-03-26

Applicant: DASSAULT AVIATION

Inventor： Sebastien Dupont de Dinechin

IPC: G01P21/00 ,  G01C23/00 ,  B64D43/00

CPC classification number: G01C23/00 ,  B64D43/00

Abstract: A device for displaying flight characteristics of an aircraft is provided. The device includes a display for the selective display of flight characteristics of an aircraft, as a function of a state of credibility assigned to measurements from static pressure, total pressure and angle-of-attack sensors, configured for selectively displaying a primary set of flight characteristics comprising at least one flight characteristic coming from a measurement from one of said sensors, when the measurements from said sensors are deemed reliable, and a secondary set of flight characteristics, distinct from said primary set, comprising at least one secondary flight characteristic designed to replace a counterpart flight characteristic from the primary set, when the measurements from at least one sensor are deemed unreliable, said secondary flight characteristic being independent of any measurement by the or each sensor deemed unreliable done when the measurements from that sensor are deemed unreliable.

Abstract translation: 提供了一种用于显示飞行器飞行特性的装置。 该装置包括用于选择性地显示飞行器的飞行特性的显示器，作为分配给静态压力，总压力和迎角传感器的测量值的可信度状态的函数，被配置用于选择性地显示主要飞行组 特征包括来自所述传感器之一的测量的至少一个飞行特征，当来自所述传感器的测量被认为是可靠的，并且与所述主组不同的第二组飞行特征包括至少一个二次飞行特性，其被设计为 当来自至少一个传感器的测量值被认为不可靠时，替换相对应的飞行特性，当从该传感器的测量被认为不可靠时，所述次要飞行特性与被认为不可靠的任何测量无关。

公开(公告)号：US20170026809A1

公开(公告)日：2017-01-26

申请号：US15211528

申请日：2016-07-15

Applicant: DASSAULT AVIATION

Inventor： Stéphane GOUVERNEUR

IPC: H04W4/04 ,  H04L29/12

CPC classification number: H04W4/40 ,  H04B7/185 ,  H04L61/605 ,  H04W4/046 ,  H04W76/15 ,  H04W84/06 ,  H04W88/02

Abstract: A communication method between an embedded communication system of an aircraft and a communication device is provided. The method includes a step for establishing a communication between the embedded communication system and the communication device, done according to a communication parameter associated with the communication device, contained in a memory of a communication terminal. The establishment step includes a phase for establishing a first auxiliary communication between terminal and the communication system, a phase for establishing a second auxiliary communication between the terminal and the communication device, according to the communication parameter, and a phase for transferring the second auxiliary communication from the terminal toward the communication system.

Abstract translation: 提供了一种飞行器的嵌入式通信系统和通信设备之间的通信方法。 该方法包括根据通信终端的存储器中包含的与通信设备相关联的通信参数来建立嵌入式通信系统和通信设备之间的通信的步骤。 该建立步骤包括用于建立终端与通信系统之间的第一辅助通信的阶段，根据通信参数建立终端和通信设备之间的第二辅助通信的阶段，以及用于传送第二辅助通信的阶段 从终端到通信系统。

公开(公告)号：US20160376027A1

公开(公告)日：2016-12-29

申请号：US15189923

申请日：2016-06-22

Applicant: DASSAULT AVIATION

Inventor： Sébastien LEPAGE ,  Olivier BAUDSON ,  Arnaud TURPIN

IPC: B64D45/08 ,  G09G3/00 ,  G02B27/01 ,  G08G5/00 ,  G08G5/02

CPC classification number: B64D45/08 ,  B64C33/02 ,  G01C23/005 ,  G02B27/0101 ,  G02B2027/014 ,  G05D1/0676 ,  G08G5/0086 ,  G08G5/025 ,  G09G3/002 ,  G09G2380/12

Abstract: A display system of an aircraft, able to display a horizon line able to be deformed and related method are provided. The display system includes a display unit; and an assembly for generating a display on the display unit, able to dynamically display, on the display unit, at least one horizon line and a slope scale relative to the horizon line. Upon approaching a landing strip, the display generator is able to create, on the horizon line, a region that is deformed as a function of the topographical slope of the landing strip approached by the aircraft.

Abstract translation: 提供了能够显示能够变形的水平线的相关方法的飞机的显示系统。 显示系统包括显示单元; 以及用于在显示单元上生成显示器的组件，其能够在显示单元上动态地显示相对于地平线的至少一个水平线和斜率。 在接近着陆带时，显示发生器能够在地平线上创建根据飞机接近的着陆带的地形坡度变形的区域。

公开(公告)号：US09529429B2

公开(公告)日：2016-12-27

申请号：US14017459

申请日：2013-09-04

Applicant: DASSAULT AVIATION

Inventor： Cyril Saint-Requier ,  Audren Kervella

IPC: G06F3/01 ,  G06F3/147 ,  B64D43/00 ,  G06F3/0354 ,  G06F3/0481

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：US20160340041A1

公开(公告)日：2016-11-24

申请号：US15160251

申请日：2016-05-20

Applicant: DASSAULT AVIATION

Inventor： Denis PEUZIAT

IPC: B64D11/00 ,  F16M13/02 ,  B64D11/06

CPC classification number: B64D11/0015 ,  B60R11/0235 ,  B64D11/06 ,  F16M11/14 ,  F16M11/2064 ,  F16M13/02 ,  F16M2200/065 ,  F16M2200/08

Abstract: A retractable support for a screen, and interior layout assembly for an aircraft cabin comprising such a support are provided. The retractable support for a screen includes a housing for receiving the screen in a retracted position, and an arm movably mounted relatively to the housing between a retracted position inside the housing and a deployed position outside the housing. The arm includes first and second rigid segments jointed with each other so that the second segment pivots relatively to the first segment around a first pivot axis between a compact configuration, in which the second segment is fitted into a recess of the first segment, and an extended configuration, in which the second segment extends out of said recess.

Abstract translation: 提供了一种用于屏幕的伸缩支撑件，以及用于包括这种支撑件的飞机机舱的内部布置组件。 屏幕的可伸缩支撑件包括用于在缩回位置接收屏幕的壳体，以及在壳体内的缩回位置和壳体外部的展开位置之间相对于壳体可移动地安装的臂。 臂包括彼此接合的第一和第二刚性部分，使得第二部分围绕第一枢转轴线相对于第一部分枢转，在紧凑构型之间，第二部分嵌入第一部分的凹部中， 延伸构造，其中第二段延伸出所述凹部。

公开(公告)号：US09483885B2

公开(公告)日：2016-11-01

申请号：US14316441

申请日：2014-06-26

Applicant: DASSAULT AVIATION

Inventor： Francois-Xavier D'Arbonneau ,  Olivier Breton

IPC: G07C5/00 ,  G07C5/08 ,  G01P5/16 ,  G01P21/02 ,  B64D45/00

CPC classification number: G07C5/0816 ,  B64D45/00 ,  G01P5/16 ,  G01P21/025

Abstract: A method for detecting a failure of at least one sensor onboard an aircraft implementing wind detection is provided. The method includes measuring an airspeed of the aircraft; measuring a geographical speed of the aircraft; determining an instantaneous wind vector, based on the measured airspeed and geographical speed; establishing an instantaneous wind variation vector, based on the determined instantaneous wind vector; projecting the instantaneous wind variation vector on the direction of the vector of an air or geographical speed of the aircraft; and determining the presence of a failure based on the obtained projection.

Abstract translation: 提供一种用于检测执行风检测的飞行器上的至少一个传感器的故障的方法。 该方法包括测量飞行器的空速; 测量飞机的地理速度; 基于测量的空速和地理速度确定瞬时风向量; 基于确定的瞬时风矢量建立瞬时风向量; 将瞬时风力变化矢量投影到飞行器的空气或地理速度的矢量的方向上; 以及基于所获得的投影来确定故障的存在。

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。

公开(公告)号：US09444391B2

公开(公告)日：2016-09-13

申请号：US14495445

申请日：2014-09-24

Applicant: DASSAULT AVIATION

Inventor： Jean-Marc Le Peuvedic

IPC: H02P6/10 ,  H02P29/02 ,  F01D15/10 ,  F02C7/32

CPC classification number: H02P29/02 ,  F01D15/10 ,  F02C7/32 ,  F05D2220/76 ,  F05D2270/335 ,  Y02T50/671

Abstract: A protective method is provided against torque peaks between a motor adapted for setting a shaft of the motor into rotation and an electric source adapted for electrically powering an electric assembly and including a fixed section and a rotating adapted for rotating with the shaft. The method includes a step for controlling the operation of the electric source forcing the rotary movement of the rotating section with the shaft to observe an instruction relating to the torque of the rotating section applied to the shaft of the motor, the instruction being adapted depending on at least one element characterizing a current operating state of the motor.

Abstract translation: 提供了一种保护方法，用于在适于将电机的轴设置为旋转的电动机和适于为电气组件供电并包括固定部分和适于与轴一起旋转的旋转的电源之间的扭矩峰值。 该方法包括用于控制电源的操作的步骤，用于迫使旋转部分与轴的旋转运动，以观察与施加到电动机的轴的旋转部分的转矩相关的指令，该指令根据 至少一个表征电动机的当前操作状态的元件。