公开(公告)号：US12214864B2

公开(公告)日：2025-02-04

申请号：US18373276

申请日：2023-09-27

Applicant: DASSAULT AVIATION

Inventor： Xavier Bernard ,  Zdenek Johan ,  Aurélien Merlet

IPC: B64C23/06 ,  B64C1/26

Abstract: An aircraft portion with reduced drag includes a wing-fuselage junction fairing at the interface between the wing and the fuselage. The junction fairing has an outer surface including two lateral portions each covering the root of a respective wing, and a lower portion connecting the side portions to each other and extending under the fuselage. The flow of air around the junction fairing during the movement of the aircraft generates at least two vortices induced on both sides, respectively, of a median longitudinal plane. The aircraft portion also includes at least two vortex generating devices extending from the lower portion of the outer surface of the junction fairing on both sides, respectively, of the median longitudinal plane.

公开(公告)号：US20240239479A1

公开(公告)日：2024-07-18

申请号：US18415055

申请日：2024-01-17

Applicant: DASSAULT AVIATION

Inventor： Eric GRANIER ,  Xavier LE ROUX

IPC: B64C13/50

CPC classification number: B64C13/504 ,  B64C13/505

Abstract: A servocontrol for controlling the position of a moving part of an aircraft made in two distinct materials including a power device comprising at least one hydraulic cylinder and a piloting device configured to control the power device according to a command for movement of the movable element. The piloting device includes at least one piloting unit which further includes a set of electronic, mechanical and/or hydraulic accessories in fluidic communication with the hydraulic cylinder and a body delimiting a network of tubular cavities fluidically connecting the accessories and the hydraulic accessories. At least part of the hydraulic cylinder is made of a first material, the body of the piloting unit being made of a second material distinct from the first material.

公开(公告)号：US20240239478A1

公开(公告)日：2024-07-18

申请号：US18415005

申请日：2024-01-17

Applicant: DASSAULT AVIATION

Inventor： Xavier LE ROUX

IPC: B64C13/50

CPC classification number: B64C13/504

Abstract: A servocontrol for controlling the position of a moving part of an aircraft includes a piloting device configured to control a power device according to a displacement control, the piloting device including a piloting unit further including a set of electronic, mechanical and/or hydraulic accessories in fluidic communication with the hydraulic cylinder and a body delimiting a network of tubular cavities fluidically connecting the electronic, mechanical and/or hydraulic accessories. The body includes an external surface, at least a first coupling portion between the network and a hydraulic cylinder and at least a second coupling portion between the network and the hydraulic cylinder and a neutral axis being defined for each tubular cavity. The neutral axis of at least one tubular cavity is curved.

公开(公告)号：US20240192696A1

公开(公告)日：2024-06-13

申请号：US18534139

申请日：2023-12-08

Applicant: DASSAULT AVIATION

Inventor： Lauren DARGENT ,  Hervé GIROD ,  Valentin RICHARD

IPC: G05D1/222

CPC classification number: G05D1/222

Abstract: A control system includes a modal state change detection module configured to receive distinct modal inputs. The detection module is configured to detect a discrete state change of each modal input and to determine data characteristics of the current discrete state. The detection module also is configured to detect a user request. The control system also includes a multimodal interpretation module configured, on each detected state change, to store and update the data characteristics of the current discrete state of the modal input following the detected state change. The multimodal interpretation module is configured, on each detected incomplete request, to complete the incomplete request from the stored up-to-date characteristic data of the current discrete state of another modal input.

公开(公告)号：US11745849B2

公开(公告)日：2023-09-05

申请号：US17560625

申请日：2021-12-23

Applicant: DASSAULT AVIATION

Inventor： Aurélien Merlet ,  Zdenek Johan ,  Ximun Loyatho ,  Gilbert Roge

IPC: B64C3/14 ,  B64C7/00 ,  B64C1/26 ,  B64C23/04 ,  B64C3/32

CPC classification number: B64C3/14 ,  B64C1/26 ,  B64C3/32 ,  B64C7/00 ,  B64C23/04 ,  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.

公开(公告)号：US20230202672A1

公开(公告)日：2023-06-29

申请号：US18087077

申请日：2022-12-22

Applicant: DASSAULT AVIATION

Inventor： Cyrille SAINT REQUIER ,  Samuel GRIMON ,  Valentin LIGIER ,  Guillaume REYDELLET

IPC: B64D43/00

CPC classification number: B64D43/00

Abstract: A virtualized aircraft control architecture includes a human-machine interface configured for generating a main command for arranging a functional element into a target configuration among a plurality of configurations; a procedure management module configured for generating a suggested command depending upon a current step of a flight procedure; a command confirmation module generating a safety command associated with the main command when the latter corresponds to the suggested command; and an interface module configured for sending the main and safety commands to a control module. The control module arranges the functional element into the target configuration when the main command and the safety command, respectively, correspond to the expected main and safety commands for arranging the functional element into the target configuration.

公开(公告)号：US20230123233A1

公开(公告)日：2023-04-20

申请号：US17967601

申请日：2022-10-17

Applicant: DASSAULT AVIATION

Inventor： Benoît URIEN ,  Cyrille GRIMALD

IPC: G08G5/00 ,  G01C21/20 ,  B64D45/00

Abstract: An aircraft mission calculation system is for indicating a risk of loss of optimality of the trajectory actually flown by the aircraft. The system includes a first trajectory calculation module, configured to calculate an optimal mission trajectory between a geographical point of origin and a geographical point of destination. The first calculation module is configured to calculate a plurality of iso-displacement curves from the geographical point of origin to the geographical point of destination. The system comprises a module for determining a level of risk of loss of optimality of the trajectory actually taken by the aircraft, associated with a modification of the trajectory of the aircraft with respect to the calculated mission trajectory, the display manager displaying on the display, in addition to the calculated trajectory, an indicator of the determined level of risk.

公开(公告)号：US20220069900A1

公开(公告)日：2022-03-03

申请号：US17409000

申请日：2021-08-23

Applicant: DASSAULT AVIATION

Inventor： Charles DELACROIX ,  Hugues ABRASSART

IPC: H04B7/185 ,  H04W40/24

Abstract: A standardized connection interface between aircraft equipment and a wireless data transmission network external to the aircraft includes a router. The router includes a mapping table between a plurality of connectivity link classes and one or more connectivity links associated with each connectivity link class. The router is configured to transmit the list of active connectivity link classes to each item of equipment, to establish a transmission of data between the piece of equipment and at least one wireless data transmission network (14A to 14E) through an active connectivity link, based on the list of active connectivity link classes and a list of connectivity link classes to which the piece of equipment is authorized to connect.

公开(公告)号：USD933790S1

公开(公告)日：2021-10-19

申请号：US29647884

申请日：2018-05-16

Applicant: DASSAULT AVIATION

Designer： Maxime Robert ,  Jean-Remi Billon

公开(公告)号：US20210123278A1

公开(公告)日：2021-04-29

申请号：US17077518

申请日：2020-10-22

Applicant: DASSAULT AVIATION

Inventor： Patrick CHAMBERS

IPC: E05D15/20 ,  B64C1/14 ,  B64D11/00 ,  B64D41/00 ,  E05D15/56 ,  E05D15/24 ,  E05F15/681

Abstract: An aircraft door mechanism includes an aircraft structure (14) delimiting an opening (24); an aircraft door (26) movable between a position closing off the opening (24) and a released position of the opening (24); and a guide system (28) for moving the door (26) between the closed off and released positions. The guide system (28) includes a main rail (46) that is fixed relative to the structure and a main carriage (48) mechanically connected to the door (26) and able to slide on the main rail (46) during the movement between said closed off and released positions. The main rail (46) is positioned between the door (26) and the structure during at least part of the movement of the door (26) between said closed off and released positions.