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.

公开(公告)号：US10513336B2

公开(公告)日：2019-12-24

申请号：US15160235

申请日：2016-05-20

Applicant: DASSAULT AVIATION

Inventor： Denis Peuziat

IPC: B64D11/00 ,  B60R11/02 ,  F16M11/04 ,  F16M13/02 ,  B64D11/06 ,  F16M11/14 ,  F16M11/20 ,  F16M11/24 ,  B60R11/00

Abstract: A retractable support for a screen, and aircraft cabin seat including such a support are provided. The retractable support for a screen comprises a support arm for the screen and a housing for receiving the arm in a retracted position inside the housing. The housing comprises a mechanism for deploying the arm outside the housing. The support further comprises a compartment defining a cavity for receiving the housing in a retracted position inside the compartment. The housing is mounted movably relative to the compartment between the retracted position and a free position outside the compartment.

公开(公告)号：US10464672B2

公开(公告)日：2019-11-05

申请号：US15402740

申请日：2017-01-10

Applicant: DASSAULT AVIATION

Inventor： Sandrine Viaud ,  Sylvain Durand

IPC: B64D1/02 ,  B64C1/14 ,  B64D25/08 ,  B63C9/01

Abstract: A system for dropping a package from an aircraft, a related aircraft and a method are provided. The system includes a panel configured to form part of a skin of the aircraft, the panel defining a through opening emerging outside the aircraft; a removable hatch and a sleeve guiding the hatch through the panel. The guide sleeve defines the through opening. The hatch is configured to be maneuvered in the guide sleeve between a configuration closing the through opening and a configuration allowing the package to pass through the through opening.

公开(公告)号：US20190279517A1

公开(公告)日：2019-09-12

申请号：US16290669

申请日：2019-03-01

Applicant: DASSAULT AVIATION

Inventor： Stéphane PICAUT

IPC: G08G5/02 ,  G01C21/10 ,  G01C21/20

Abstract: A dynamic determination method for determining the position of a stopping point of an aircraft on a landing strip and related system includes determining a first table of average time from touchdown of the aircraft as a function of the ground speed, based on an average deceleration profile of the aircraft; determining a first deceleration profile adapted to the current conditions, based on an engine thrust computed for each ground speed from the average time determined in the first table; determining a second table of time adapted to the current conditions based on the first deceleration profile; determining a second deceleration profile adapted to the current conditions, based on an engine thrust computed for each ground speed from the time determined in the second table; and computing the position of the stopping point from the second adapted deceleration profile.

公开(公告)号：US10403274B2

公开(公告)日：2019-09-03

申请号：US15264722

申请日：2016-09-14

Applicant: DASSAULT AVIATION

Inventor： Hervé Girod ,  Paul Kou ,  Jean-François Saez

IPC: G10L15/22 ,  B64C39/02 ,  G06F3/01 ,  B64D43/00 ,  G10L15/18 ,  G10L15/02 ,  G10L15/187

Abstract: An automatic speech recognition with detection of at least one contextual element, and application to aircraft flying and maintenance are provided. The automatic speech recognition device comprises a unit for acquiring an audio signal, a device for detecting the state of at least one contextual element, and a language decoder for determining an oral instruction corresponding to the audio signal. The language decoder comprises at least one acoustic model defining an acoustic probability law and at least two syntax models each defining a syntax probability law. The language decoder also comprises an oral instruction construction algorithm implementing the acoustic model and a plurality of active syntax models taken from among the syntax models, a contextualization processor to select, based on the state of the order each contextual element detected by the detection device, at least one syntax model selected from among the plurality of active syntax models, and a processor for determining the oral instruction corresponding to the audio signal.

公开(公告)号：US10310920B2

公开(公告)日：2019-06-04

申请号：US15058895

申请日：2016-03-02

Applicant: DASSAULT AVIATION

Inventor： Benjamin Briand

IPC: G06F9/54 ,  G08G5/00 ,  G06F16/22 ,  G06F16/23

Abstract: A management method is provided for managing data relative to an aircraft mission comprising at least one flight by an aircraft, the data comprising input data of at least two applications and output data of the applications, each application being able to be executed by a computer to determine, from the input data of the application, the output data. The method includes a step for providing a set of generic data, each of the generic data being an input datum shared by at least two of the applications, a step for assigning a value to at least one of the generic data for at least one flight of the mission, and a step for configuring the applications comprising the automatic assignment, to each input datum corresponding to a generic datum, of the value of the generic datum.

公开(公告)号：US20190122572A1

公开(公告)日：2019-04-25

申请号：US16168799

申请日：2018-10-23

Applicant: DASSAULT AVIATION

Inventor： Olivier MORELLEC ,  François SALMON-LEGAGNEUR

IPC: G08G5/06 ,  B64C25/50 ,  G05D1/02

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 said current trajectory and at least one limit curve (204a, 204b, 206a, 206b) representative of the limit trajectory, superimposed on the view (200).