公开(公告)号：US20210122473A1

公开(公告)日：2021-04-29

申请号：US17077684

申请日：2020-10-22

Applicant: DASSAULT AVIATION

Inventor： Lionel Patrick GERME ,  Emmanuel PICUT ,  Alain LEVAVASSEUR ,  Erwan BOULO ,  Jérémie GUERARD

IPC: B64D11/06 ,  B64D41/00

Abstract: An aircraft cabin includes at least one seat able to receive at least one passenger; at least one table arranged opposite the seat; and a safety device able to be mounted on the table, below the table or received in the table. The safety device includes a deployable protection assembly including an airbag deployable from a retracted idle configuration to a deployed safety configuration, and a system for controlling the deployment of the or each airbag, able to trigger the deployment of the airbag beyond a threshold deceleration value of the aircraft.

公开(公告)号：US20210061468A1

公开(公告)日：2021-03-04

申请号：US17003675

申请日：2020-08-26

Applicant: DASSAULT AVIATION

Inventor： Maxime ROBERT ,  Agnès GERVAIS

IPC: B64D11/00

Abstract: The cabin includes a rear compartment including at least one luggage storage area and/or a lavatory, a main compartment including a plurality of seats, and an intermediate compartment. The intermediate compartment includes, on either side of the fuselage, isolation areas, and a central passageway, having a width greater than 50.8 cm. Each isolation area includes a seat and longitudinal partitions delimiting an access opening to the isolation area. Each seat is maneuverable between a retracted seating position for an occupant of the isolation area and an extended lying position of an occupant of the isolation area.

公开(公告)号：US10908767B2

公开(公告)日：2021-02-02

申请号：US16711244

申请日：2019-12-11

Applicant: DASSAULT AVIATION

Inventor： Sébastien Lepage ,  Hasna Nadfaoui

IPC: G01P1/10 ,  G06F3/0481 ,  G01C23/00 ,  B64D43/00 ,  B64D43/02

Abstract: A display device for displaying information relative to a flight by an aircraft is provided. The information includes information relative to an energy variation of the aircraft, the energy variation being expressed by a variable representative of that energy variation. The display device is configured to show, on a viewing screen, an energy variation symbol representative of a current value of the variable. The display device is configured to further show at least one energy variation bound symbol representative of a threshold value of the variable, the threshold value corresponding to an authorized acceleration bound for the aircraft to keep or bring the speed of the aircraft in or toward a predefined usage speed range.

公开(公告)号：US10895948B2

公开(公告)日：2021-01-19

申请号：US16711206

申请日：2019-12-11

Applicant: DASSAULT AVIATION

Inventor： Sébastien Lepage ,  Hasna Nadfaoui

IPC: B64D45/08 ,  G06F3/0481 ,  G01C23/00 ,  B64D43/00 ,  B64D43/02

Abstract: A display device for displaying information relative to a flight by an aircraft is provided. The information includes information relative to an energy variation of the aircraft, the energy variation being expressed by a variable representative of that energy variation. The display device is configured to show, on a viewing screen, an energy variation symbol representative of a current value of the variable. The display device is configured to further show at least one energy variation bound symbol representative of a threshold value of the variable, the threshold value corresponding to an authorized acceleration bound for the aircraft to keep or bring the speed of the aircraft in or toward a predefined usage speed range.

公开(公告)号：US10882631B2

公开(公告)日：2021-01-05

申请号：US15809385

申请日：2017-11-10

Applicant: DASSAULT AVIATION

Inventor： Eric Granier ,  Jérôme Le Borloch

IPC: B64D31/04 ,  B64D31/14 ,  B64C13/50

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：US10822117B2

公开(公告)日：2020-11-03

申请号：US15589940

申请日：2017-05-08

Applicant: DASSAULT AVIATION

Inventor： Marc Chaduc ,  Sylvain Mateus

IPC: B64D47/08 ,  B64C1/14 ,  H04N7/18 ,  G01J5/00

Abstract: An observation system for an aircraft, related aircraft and method are provided. The observation system includes an observation assembly deployable between a retracted inner position and a deployed outer position outside a passage opening and a deployment mechanism of the observation assembly. The system includes a hatch, mounted moving between a position closing off the passage opening and a position clearing the passage opening, and a mechanism for maneuvering the hatch between the closing off position and the clearing position. The system also includes a conjugating assembly between the mechanism for deploying the observation assembly and the mechanism for maneuvering the hatch, active over at least part of the movement of the observation assembly between the retracted position and the deployed position, to move the hatch from the closing off position to the clearing position during the movement.

公开(公告)号：US20200269982A1

公开(公告)日：2020-08-27

申请号：US16792488

申请日：2020-02-17

Applicant: DASSAULT AVIATION

Inventor： Christophe HARROIS ,  Jean-Rémi BILLON ,  Séverine ASFAUX

IPC: B64D11/00 ,  B64D11/04 ,  B64C1/14

Abstract: An aircraft (10) includes a fuselage (12) delimiting a cockpit (14), a passenger entry area (18) and a passenger cabin (16) configured to accommodate passengers during a flight phase. The entry area (18) is interposed longitudinally between the cockpit (14) and the cabin. The cockpit and the entry area are delimited by a front separating element (24) and the entry area and the cabin are delimited by a rear separating element (26). The fuselage delimits a side boarding door (20). A transverse median plane (66) of the boarding door is placed at a distance from the front separating element, considered along the longitudinal axis, greater than 39% of the length between the front separating element and the rear separating element, considered along the longitudinal axis.

公开(公告)号：US20200247530A1

公开(公告)日：2020-08-06

申请号：US16781266

申请日：2020-02-04

Applicant: DASSAULT AVIATION

Inventor： Sylvain HUET

IPC: B64C13/50

Abstract: A method for controlling a play in a flight control surface (12) of an aircraft, implemented by a control system, includes sending a sinusoidal excitation signal; measuring a response signal corresponding to the evolution of a parameter representative of the response of the flight control surface (12) to the sinusoidal excitation signal; processing the response signal to determine the play in the flight control surface (12). The processing includes determining a characteristic variable of an odd harmonic of the response signal other than the first harmonic of the response signal; and determining the play from the characteristic variable with an abacus curve.

公开(公告)号：US10580316B2

公开(公告)日：2020-03-03

申请号：US16168799

申请日：2018-10-23

Applicant: DASSAULT AVIATION

Inventor： Olivier Morellec ,  François Salmon-Legagneur

IPC: G08B21/00 ,  G08G5/06 ,  B64C25/50 ,  G05D1/02 ,  B64C25/34 ,  B64D43/00

Abstract: A system for controlling a trajectory of an aircraft on the ground, includes a determining module configured to determine a current trajectory of the aircraft on the ground including a series of waypoints planned for an element of the aircraft with unchanged conditions of the lateral movement devices of the aircraft, and at least one limit trajectory, including a series of limit waypoints that may be reached by the element by actuating at least one lateral movement device. The system includes a display assembly comprising a viewer configured to display a view (200) of a runway portion located near the aircraft, and a display generating module configured to display, on the viewer, a current trajectory curve (202) representative of the current trajectory and at least one limit curve (204a, 204b, 206a, 206b) representative of the limit trajectory, superimposed on the view (200).

公开(公告)号：US20200020237A1

公开(公告)日：2020-01-16

申请号：US16508263

申请日：2019-07-10

Applicant: DASSAULT AVIATION

Inventor： Cyrille GRIMALD ,  Benoit URIEN

IPC: G08G5/00

Abstract: A system for calculating a mission of an aircraft by combination of algorithms includes a first path calculation module, configured for calculating an optimal mission path between a geographical point of origin and a geographical destination point as a function of airplane performance, operational mission specifications and a weather context. The first calculation module is configured to determine the optimal path in a manner non constrained by a network of waypoints and/or imposed paths between the waypoints. The system includes a definition module, around the optimal path, an optimization region of the path and a second path calculating module, configured to calculate an optimized path of the aircraft in the optimization region in a manner constrained by a network of waypoints and/or imposed paths between the waypoints.