公开(公告)号：US10187487B2

公开(公告)日：2019-01-22

申请号：US14865922

申请日：2015-09-25

Applicant: DASSAULT AVIATION

Inventor： Adrien Drion ,  Arnaud Hennequin

IPC: H04L29/08 ,  G06F8/60 ,  H04B7/185

Abstract: An infrastructure for hosting services in an aircraft, and related access method are provided. The infrastructure includes a plurality of onboard platforms, each platform corresponding to a functional domain of the aircraft and hosting at least one service able to be implemented in the aircraft in the functional domain in question; at least one onboard communicator communicating with a ground structure, connected to each onboard platform; and at least one access portal able to allow centralized access to services hosted by all of the onboard platforms corresponding to the different functional domains of the aircraft.

公开(公告)号：USD830076S1

公开(公告)日：2018-10-09

申请号：US29603954

申请日：2017-05-15

Applicant: DASSAULT AVIATION

Designer： Faustine Amiard ,  Caroline Larmaraud ,  Thomas Guillard

公开(公告)号：US20180155671A1

公开(公告)日：2018-06-07

申请号：US15804227

申请日：2017-11-06

Applicant: DASSAULT AVIATION

Inventor： Jean-Philippe DUPONT ,  Marc CATHELAIN

IPC: C12M1/34 ,  B64D37/02 ,  C12Q1/04 ,  G01F23/292

CPC classification number: C12M41/36 ,  B64D37/005 ,  B64D37/02 ,  B64D37/32 ,  C12Q1/04 ,  G01F23/2922

Abstract: Aircraft fuel tank, which has a visual control system inside the tank, includes at least a side wall (12), an upper wall (14) and a lower wall (16), the tank (10) comprising a visual inspection system (22) inside the tank (10). The visual inspection system (22) includes an inspection eyepiece (24) arranged in one of the walls (12, 14, 16), a light inlet (26) arranged in one of the walls (12, 14, 16) and configured to allow light from an artificial light source (30) situated outside the tank (10) to enter the tank (10), and a light guide (28) protruding inside the tank (10) from the light inlet (26) to guide the light produced by the artificial light source (30) to the inside of the tank (10).

公开(公告)号：US20180155008A1

公开(公告)日：2018-06-07

申请号：US15809388

申请日：2017-11-10

Applicant: DASSAULT AVIATION

Inventor： Jérôme LE BORLOCH

IPC: B64C13/04 ,  G05G1/04

CPC classification number: B64C13/0425 ,  B64D31/04 ,  B64D43/00 ,  B64D45/00 ,  G05G1/04

Abstract: A device for managing the mechanical energy of an aircraft, having a light system, includes a support defining a guide; at least one control lever for varying the mechanical energy of the aircraft, mounted moving through the guide; and at least one position sensor detecting the position of the control lever in the guide, configured to create position information for the position of the control lever in the guide intended to be sent to a flight control unit of the aircraft. The device also includes at least one light strip extending on the support along at least part of the travel of the control lever in the guide; and a control unit of the at least one light strip, configured to display at least one light indication at least at one given point of the lighted position ramp calculated as a function of a movement context of the aircraft.

公开(公告)号：US20180134404A1

公开(公告)日：2018-05-17

申请号：US15809385

申请日：2017-11-10

Applicant: DASSAULT AVIATION

Inventor： Eric GRANIER ,  Jérôme LE BORLOCH

IPC: B64D31/04

CPC classification number: B64D31/04 ,  B64C13/503 ,  B64C13/506 ,  B64C13/507 ,  B64D31/14

Abstract: A device for managing the mechanical energy of an aircraft, with a force application system on a control lever, includes a support defining a guide; a moving control lever for controlling varying a mechanical energy variation of the aircraft, mounted moving through the guide; and at least one position sensor detecting the position of the moving lever in the guide, configured to create position information for the position of the moving lever in the guide intended to be sent to a flight control unit of the aircraft. The device also includes an active force applicator for applying a force on the moving lever, configured to generate a force applied on the moving lever. The force depends on the position of the moving lever in the guide.

公开(公告)号：US20180134403A1

公开(公告)日：2018-05-17

申请号：US15809374

申请日：2017-11-10

Applicant: DASSAULT AVIATION

Inventor： Eric GRANIER ,  Jérôme LE BORLOCH

IPC: B64D31/04

CPC classification number: B64D31/04 ,  B64D31/14

Abstract: A device for managing the mechanical energy of an aircraft, having an energy management auxiliary system, includes a support defining a guide, a centralized control lever for varying the energy of the aircraft, at least one position sensor detecting the position of the centralized control lever in the guide. The position sensor is configured to create position information for the position of the centralized control lever in the guide intended to be sent to a flight control unit of the aircraft. The device also includes an auxiliary support; for the or each motor of the aircraft, an individual control lever for the individual propulsion of the motor, mounted movably in the auxiliary support; and at least one auxiliary position sensor detecting the position of the or each individual lever configured to generate information intended to be sent to the flight control unit of the aircraft.

公开(公告)号：US20180110334A1

公开(公告)日：2018-04-26

申请号：US15334572

申请日：2016-10-26

Applicant: DASSAULT AVIATION

Inventor： Ludovic HAMON ,  Grégory LE FLOC'H

IPC: A47B88/14 ,  A47B88/04 ,  A47B88/10

CPC classification number: A47B88/43 ,  A47B88/45 ,  A47B88/487 ,  A47B88/493 ,  A47B2210/0059 ,  A47B2210/0078

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：US09938016B2

公开(公告)日：2018-04-10

申请号：US15010696

申请日：2016-01-29

Applicant: DASSAULT AVIATION

Inventor： Nicolas Hance

IPC: B64D11/00 ,  B64D11/06

CPC classification number: B64D11/0605 ,  B64D11/0638

Abstract: A supporting device for an interior layout assembly of an aircraft cabin, a related assembly and method are provided. The device includes a stationary frame; a table that can be deployed relative to the frame between a retracted position and a horizontal deployed position; a mechanism for guiding the movement of the table relative to the frame between the retracted position and the deployed horizontal position. The guide mechanism defines at least one bearing point for the table during its passage from the retracted position to the deployed horizontal position, the bearing point having a globally invariable position relative to the frame, the table being configured to pivot on the bearing point while moving laterally away relative to the bearing point, by sliding on the bearing point, to the deployed position.

公开(公告)号：US09933451B2

公开(公告)日：2018-04-03

申请号：US14388775

申请日：2013-03-26

Applicant: DASSAULT AVIATION

Inventor： Sebastien Dupont De Dinechin

IPC: B64F5/60 ,  G01P13/02 ,  G01P21/02

CPC classification number: G01P13/025 ,  B64F5/60 ,  G01P21/025

Abstract: A method for determining a state of credibility of measurements of an angle-of-attack sensor of an aircraft is provided. This method includes at least one coherence test between angle-of-attack measurements from said angle-of-attack sensor, and the measurements of a flight characteristic of the aircraft, distinct from the angle-of-attack. The coherence test includes determining an angle-of-attack value from said angle-of-attack sensor, determining said flight characteristic of the aircraft, determining a value of at least one indicator of the coherence of the angle-of-attack value with the value of said flight characteristic, and activating a low state of credibility, in which the measurements of said angle-of-attack sensor are deemed unreliable, or an intermediate state of credibility, in which the measurements from said angle-of-attack sensor are deemed coherent with said flight characteristic, based on the value of said coherence indicator.

公开(公告)号：US20170320591A1

公开(公告)日：2017-11-09

申请号：US15582811

申请日：2017-05-01

Applicant: DASSAULT AVIATION

Inventor： Jérôme TABUTEAU ,  Jérôme BRUNET

IPC: B64D47/00 ,  B64C1/36 ,  B64D45/00

Abstract: A support device for a radio equipment of an aircraft, radio system and aircraft are provided. The support device includes a fastening structure (31), intended to be secured to a lower surface of a fuselage of an aircraft, and a support platform (33) of the radio equipment (25). The support platform (33) is mounted pivoting on the fastening structure (31) around a pivot axis (A) between an operational position and a backup position. The support device comprises a locking mechanism (56), able to be actuated from a locked configuration, in which said locking mechanism (56) keeps the support platform (33) in its operational position while preventing any pivoting of the support platform (33), to an unlocked configuration, in which the locking mechanism (56) allows the support platform (33) to pivot relative to the fastening structure (31).