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    Support for a radio equipment of an aircraft, radio system and aircraft
    31.
    发明授权
    Support for a radio equipment of an aircraft, radio system and aircraft 有权

    公开(公告)号：US10513348B2

    公开(公告)日：2019-12-24

    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 ,  H01Q1/28 ,  H01Q1/12 ,  H01Q1/42 ,  H01Q3/06

    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).

    RADOME COMPRISING A LAMINATE STRUCTURE COMPRISING COMPOSITE LAYERS WHOSE FIBER REINFORCEMENT CONSISTS OF POLYOLEFIN FIBERS
    32.
    发明申请
    RADOME COMPRISING A LAMINATE STRUCTURE COMPRISING COMPOSITE LAYERS WHOSE FIBER REINFORCEMENT CONSISTS OF POLYOLEFIN FIBERS 审中-公开

    公开(公告)号：US20190381760A1

    公开(公告)日：2019-12-19

    申请号：US16434199

    申请日：2019-06-07

    Applicant: DASSAULT AVIATION

    Inventor： Olivier CALVO PEREZ ,  Benoit BERTON

    IPC: B32B5/26

    Abstract: A radome includes a laminated structure (42) in the form of a stack of composite layers (44, 46, 48, 50), each composite layer (44, 46, 48, 50) including a fibrous reinforcement mixed with an organic matrix. The composite layers includes at least one high-permittivity layer (44, 50), including a structural layer (44), and a plurality of low-permittivity layers (46, 48), including two covering layers (46, 48) sandwiching the structural layer (44) between them, each of the covering layers (46, 48) having a lower thickness to the thickness of the structural layer (44). In each low-permittivity layer (46, 48), the fibrous reinforcement includes a majority of polyolefin fibers.

    AIRCRAFT PORTION WITH REDUCED WAVE DRAG
    33.
    发明申请
    AIRCRAFT PORTION WITH REDUCED WAVE DRAG 审中-公开

    公开(公告)号：US20190248467A1

    公开(公告)日：2019-08-15

    申请号：US16261486

    申请日：2019-01-29

    Applicant: DASSAULT AVIATION

    Inventor： Aurélien MERLET ,  Zdenek JOHAN ,  Ximun LOYATHO ,  Gilbert ROGE

    IPC: B64C3/14 ,  B64C3/32

    CPC classification number: B64C3/14 ,  B64C1/26 ,  B64C3/32 ,  B64C7/00 ,  B64C2003/149

    Abstract: An aircraft portion includes a fuselage oriented in a longitudinal direction, an airfoil made up of at least one pair of wings arranged on either side of the fuselage in a transverse direction orthogonal to the longitudinal direction, and an airfoil-fuselage junction fairing at the interface between the airfoil and the fuselage. The junction fairing has, in a vertical plane, a lower profile and, in a horizontal plane, a horizontal profile at the junction of the outer surface of the junction fairing with the convex side of each wing. The horizontal profile and/or the lower profile successively has, in the longitudinal direction, a convex front segment, a concave intermediate segment, and a convex rear segment.

    System for displaying information related to a flight of an aircraft and associated method
    34.
    发明授权
    System for displaying information related to a flight of an aircraft and associated method 有权

    公开(公告)号：US10339820B2

    公开(公告)日：2019-07-02

    申请号：US15158807

    申请日：2016-05-19

    Applicant: DASSAULT AVIATION

    Inventor： Arnaud Branthomme ,  Igor Fain ,  Patrick Darses

    IPC: G08G5/00 ,  G01C23/00 ,  B64D43/00 ,  G06T15/20 ,  G09G5/377

    Abstract: A system for displaying information related to a flight of an aircraft and an associated method are provided. The display system comprises a display device, a man-machine interface, a module for dynamically generating synthesis images, each comprising a synthetic depiction of the environment and a curve representative of a trajectory, said module being configured to generate a first synthesis image centered around a first central point of interest, to command the display thereof, and to detect an action to modify the central point of interest by an operator via said man-machine interface. The generating module is also configured to determine, as a function of said modification action, a second central point of interest, situated along said curve whatever said modification action is, to generate a second synthesis image centered around said second central point of interest, and to command the display thereof.

    Infrastructure for hosting services in an aircraft, and related access method
    35.
    发明授权
    Infrastructure for hosting services in an aircraft, and related access method 有权

    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.

    DEVICE FOR MANAGING THE MECHANICAL ENERGY OF AN AIRCRAFT, HAVING A LIGHT SYSTEM, RELATED AIRCRAFT AND PROCESS
    38.
    发明申请
    DEVICE FOR MANAGING THE MECHANICAL ENERGY OF AN AIRCRAFT, HAVING A LIGHT SYSTEM, RELATED AIRCRAFT AND PROCESS 审中-公开

    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.

    DEVICE FOR MANAGING THE MECHANICAL ENERGY OF AN AIRCRAFT, HAVING AN ENERGY MANAGEMENT AUXILIARY SYSTEM, RELATED AIRCRAFT AND PROCESS
    40.
    发明申请
    DEVICE FOR MANAGING THE MECHANICAL ENERGY OF AN AIRCRAFT, HAVING AN ENERGY MANAGEMENT AUXILIARY SYSTEM, RELATED AIRCRAFT AND PROCESS 审中-公开

    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.

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