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

公开(公告)号：US10118703B2

公开(公告)日：2018-11-06

申请号：US15489680

申请日：2017-04-17

Applicant: DASSAULT AVIATION

Inventor： Michel Mihai ,  Gaëtan Lamothe

IPC: A47C4/00 ,  B64D11/06

Abstract: Armrest for aircraft seat, associated seat and process are provided. The armrest includes a stationary part (12) intended to be connected to the seat, a moving part (14) movable relative to the stationary part (12), between a high position in which the moving part (14) is intended to protrude above a seat bottom of the seat and a low position, and a maneuvering mechanism (18) able to guide the movement of the moving part (14) between the high position and the low position. The maneuvering mechanism (18) includes at least a first connecting rod (26) and a second connecting rod (27), each independently connecting the stationary part (12) to the moving part (14), the first connecting rod (26) and the second connecting rod (27) being arranged parallel to one another during the movement of the moving part (14) between the high position and the low position.

公开(公告)号：USD830949S1

公开(公告)日：2018-10-16

申请号：US29603981

申请日：2017-05-15

Applicant: DASSAULT AVIATION

Designer： Marion D'Halluin ,  Jean-Remi Billon ,  Matthieu Poidatz ,  Agnès Gervais ,  Maxime Robert

公开(公告)号：USD830284S1

公开(公告)日：2018-10-09

申请号：US29603985

申请日：2017-05-15

Applicant: DASSAULT AVIATION

Designer： Marion D'Halluin ,  Jean-Remi Billon ,  Matthieu Poidatz ,  Agnès Gervais ,  Maxime Robert

公开(公告)号：US10078100B2

公开(公告)日：2018-09-18

申请号：US14388781

申请日：2013-03-26

Applicant: DASSAULT AVIATION

Inventor： Sebastien Dupont De Dinechin

IPC: G06F19/00 ,  G01P21/00 ,  G01P13/02 ,  G01P5/16 ,  B64D43/02 ,  G01B21/00 ,  G01G23/01 ,  G01M9/06 ,  G01P3/80

CPC classification number: G01P21/00 ,  B64D43/02 ,  G01B21/00 ,  G01G23/01 ,  G01M9/06 ,  G01P3/806 ,  G01P5/16 ,  G01P13/025

Abstract: A method for determining a state of credibility of measurements made by sensors of an aircraft is provided. This method includes determining a speed of the aircraft, from static and total pressure measurements, determining a coefficient of lift of the aircraft from an incidence measurement and from said speed, determining a weight of the aircraft, determining if an equation of lift of the aircraft is satisfied, activating a state of optimal credibility, wherein the measurements made by said sensors are considered to be reliable if the said equation of lift is satisfied, activating a state of non-optimal credibility, wherein the measurements of at least one sensor are considered to be unreliable if the said equation of lift is not satisfied.

公开(公告)号：US10038985B2

公开(公告)日：2018-07-31

申请号：US15211528

申请日：2016-07-15

Applicant: DASSAULT AVIATION

Inventor： Stéphane Gouverneur

IPC: H04W84/04 ,  H04W88/02 ,  H04B7/185 ,  H04W4/04 ,  H04W76/15 ,  H04L29/12 ,  H04W76/02 ,  H04W84/06

CPC classification number: H04W4/42 ,  H04B7/185 ,  H04L61/605 ,  H04W4/40 ,  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.

公开(公告)号：US20170313425A1

公开(公告)日：2017-11-02

申请号：US15497916

申请日：2017-04-26

Applicant: DASSAULT AVIATION

Inventor： Mathieu SENET

IPC: B64D11/00 ,  B64D45/00

CPC classification number: B64D11/0015 ,  B64D11/04 ,  B64D45/00 ,  B64D2045/007

Abstract: Avionics system for assisting implementation of security measures onboard an aircraft, aircraft comprising such a system, and associated method are provided. The avionics system is intended to assist the occupants of an aircraft in implementing security measures onboard the aircraft. It includes a parameter collector for collecting at least one avionics parameter of the aircraft, a context finder to determine a context from the or each avionics parameter collected by the collector, an instruction identifier to identify at least one relevant security instruction based on the context determined by the context finder, and at least one instruction submitter to submit the or each relevant security instruction to a passenger of the aircraft.