公开(公告)号：US10748432B2

公开(公告)日：2020-08-18

申请号：US14858751

申请日：2015-09-18

Applicant: DASSAULT AVIATION

Inventor： Jérôme Lagarde ,  Eric Boulle ,  Marie-Gabrielle Lafoucriere ,  Jérôme Barral

IPC: G06F19/00 ,  G08G5/00 ,  G01S13/95 ,  B64D45/00

Abstract: A piloting assistance system of a platform, and associated method are provided. The system includes a first detector for detecting a windshear able to generate a first alert that the platform is approaching a windshear zone; a second detector for detecting a windshear able to generate a second alert indicating the presence of the platform in the windshear zone; and a guider of the platform. The guider is able to automatically select a first guidance mode when a first alert is generated by the first detector, and to automatically select at least one second guidance mode different from the first guidance mode when a second alert is generated by the second detector. The system includes an information device able to display unified windshear alert information and/or unified information for implementation of a guidance mode, shared by the first alert and the second alert.

公开(公告)号：US20200017233A1

公开(公告)日：2020-01-16

申请号：US16508268

申请日：2019-07-10

Applicant: DASSAULT AVIATION

Inventor： Cyril SAINT REQUIER ,  Gilles CONSTANT ,  Guy SCHALLER ,  Arnaud BRANTHOMME ,  Magali THOREL

IPC: B64D45/00 ,  G08G5/00

Abstract: An aircraft operational state monitoring system is provided that includes a module for acquiring a logic state of a plurality of components of the aircraft, the components belonging to airplane systems. The aircraft operational state monitoring system includes a module for determining the operability status of a plurality of macroscopic functions of the aircraft, each macroscopic function being defined independently of the components and airplane systems necessary for the performance of the macroscopic function, the operability status being determined based on logic states of the plurality of components between an operational status and at least one nonoperational status. The aircraft operational state monitoring system includes a display and at least one graphic display management assembly on the display, configured for displaying, on the display, summary indicators of the operability status of the macroscopic functions of the aircraft.

公开(公告)号：US20190352008A1

公开(公告)日：2019-11-21

申请号：US16413768

申请日：2019-05-16

Applicant: DASSAULT AVIATION

Inventor： François-Xavier D'ARBONNEAU ,  Patrick DARSES ,  Bruno FERRY ,  François SALMON-LEGAGNEUR ,  Jean-Christophe DENJEAN

IPC: B64D11/00

Abstract: A device for waking up a crew member resting on an aircraft includes a processing unit configured to detect current development parameters of the aircraft and/or to detect a state of consciousness of at least one other active crewmember. The processing unit is also configured to activate an apparatus for waking up the resting crew member, when at least one predetermined condition for waking up the resting crew member on one or several current parameters of the aircraft and/or on a parameter representative of the state of consciousness of the at least one other active crew member is satisfied.

公开(公告)号：US10467989B2

公开(公告)日：2019-11-05

申请号：US15092838

申请日：2016-04-07

Applicant: DASSAULT AVIATION

Inventor： Arnaud Branthomme ,  Gilles Constant

IPC: G09G5/36 ,  G06F3/0482 ,  G06F3/0484 ,  G06F3/0485 ,  G06T13/80

Abstract: A system for visualizing an aircraft procedure having several alternate sequences and related process are provided. The system includes a display and a display management assembly on the display, making it possible to display successive steps of the procedure on the display. The display management assembly able to display, on the display, an active step of an active sequence of the procedure, at least one prior step preceding the active step in the active sequence of the procedure and defining one alternative among several series of steps, and at least one step after the active step in this active sequence of the procedure, without displaying a step of the procedure situated on an inactive sequence of the procedure that may be accessible from any step before the active step.

公开(公告)号：US20190164440A1

公开(公告)日：2019-05-30

申请号：US16199045

申请日：2018-11-23

Applicant: DASSAULT AVIATION

Inventor： Benjamin BRIAND ,  Cédric CARLE ,  Stéphane DRINAL ,  Cyrille GRIMALD ,  Jean-François SAEZ ,  Cyril SAINT REQUIER ,  Jean-Baptiste VALLART

IPC: G08G5/00 ,  G01C23/00

Abstract: An aircraft mission computing system includes an aircraft mission path computing engine, and a mission deck comprising a display and a display management assembly configured for displaying, on the display, at least one button for defining an operational specification of the mission. The computing engine is configured to be activated after defining the choice of operational specification using the definition button to determine at least one possible path of the aircraft based on the or each choice of defined operational specification using the or each definition button. The display management assembly is configured to display, on the display, after the activation of the computing engine, at least one outcome indicator providing mission feasibility information while respecting the or each operational specification choice.

公开(公告)号：US10295396B2

公开(公告)日：2019-05-21

申请号：US14388778

申请日：2013-03-26

Applicant: DASSAULT AVIATION

Inventor： Sebastien Dupont De Dinechin

IPC: G01G19/07 ,  G01G19/414

Abstract: A method for determining an estimated mass of an aircraft is provided. This method includes determining a first mass of the aircraft, from characteristics of the aircraft determined before or after takeoff of the aircraft, determining, during the flight of the aircraft, a second mass of the aircraft, from a lift equation of the aircraft expressing the mass of the aircraft as a function of information representative of the load factor of the aircraft, of a lift coefficient of the aircraft, of speed information of the aircraft and of a static pressure of a mass of air passed through by the aircraft, determined from measurements by sensors of the aircraft during the flight of the aircraft, evaluating the estimated mass at said determination moment, as a function of said first and second masses.

公开(公告)号：US10286994B2

公开(公告)日：2019-05-14

申请号：US14044110

申请日：2013-10-02

Applicant: DASSAULT AVIATION

Inventor： Fabien Bouffanais ,  Benoit De Maqueville ,  Olivier Gavouyere ,  Zdenek Johan

IPC: B64C1/14 ,  B64D47/08

Abstract: The nose section for a flying machine according to the invention comprises an enclosure delimiting a nose cone extending along a longitudinal axis (A-A′), the enclosure delimiting a window, and a glass closing the window extending transversely relative to the longitudinal axis (A-A′). The nose section includes an optical sensor, in particular a camera, positioned in the enclosure behind the glass. The enclosure defines a recess, the window covered by the glass being at least partially positioned in the recess.

公开(公告)号：US10285501B2

公开(公告)日：2019-05-14

申请号：US15334572

申请日：2016-10-26

Applicant: DASSAULT AVIATION

Inventor： Ludovic Hamon ,  Grégory Le Floc'h

IPC: A47B88/43 ,  A47B88/45 ,  A47B88/493 ,  A47B88/487

Abstract: A slide system for slidably opening and closing a drawer is provided. The slide system includes an outer slide for mounting the slide system on a side wall of an enclosure, comprising a longitudinal slide outer channel, a sliding member, configured to be mounted on a side wall of the drawer, slidably movable within said slide outer channel. The outer slide includes a fixing part for attachment of the outer slide on the side wall of the enclosure, a sliding part comprising said slide outer channel, and an intermediate part, extending from said fixing part to said sliding part. The fixing part, the intermediate part and the sliding part define a groove extending upwardly from said intermediate part. The slide system comprises a casing element for encasing the sliding member by extending vertically from an upper portion the side wall of the drawer towards the intermediate part of the outer slide and being at least partly received within the groove.

公开(公告)号：US20190118939A1

公开(公告)日：2019-04-25

申请号：US16168795

申请日：2018-10-23

Applicant: DASSAULT AVIATION

Inventor： Olivier CANTINAUD ,  Laurent GOERIG ,  Julien PRODIGUE

IPC: B64C25/50 ,  G08G5/06 ,  G05D1/02

Abstract: A system (40) for controlling a ground lateral trajectory of an aircraft includes a command module (120) configured to generate a command of an instruction lateral trajectory, a limiting module (58) configured to determine, as a function of a speed and a maximum authorized sideslip angle of the wheel (5) of the aircraft, a steering angle range of the wheel (5) such that, the steering angle of the wheel (5) being in this range, the steering angle of the wheel (5) is smaller than the maximum steering angle, and a control module (130) configured to determine, as a function of the command, an instruction steering angle included in the range and able to cause a lateral movement of the aircraft according to or tending toward the instruction trajectory, and to send a steering instruction to the wheel (5) in order to orient it along the instruction angle.

公开(公告)号：USD837026S1

公开(公告)日：2019-01-01

申请号：US29603961

申请日：2017-05-15

Applicant: DASSAULT AVIATION

Designer： Matthieu Poidatz ,  Agnès Gervais