公开(公告)号：US10407180B2

公开(公告)日：2019-09-10

申请号：US15364925

申请日：2016-11-30

Applicant: DASSAULT AVIATION

Inventor： Olivier Morellec ,  Philippe Vorms ,  Maxime Philbert

IPC: B64D45/00 ,  B64D43/00 ,  G06F3/01 ,  G06F3/0482 ,  G06F3/0362 ,  G08B6/00

Abstract: An interface system between a user and a display device in the cockpit of an aircraft, related aircraft and method are provided. The system includes a rotary controller configured to control a target on the display device; a target manager, controlled by the rotary controller for moving the target on the display device during the rotation of the rotary controller and/or for interacting with a field targeted by the target during the rotation of the rotary controller; a haptic feedback generator on the rotary controller during its rotation. The haptic feedback generator is configured to generate at least two distinct haptic profiles on the rotary controller depending on distinct system states and/or distinct man-machine interface states of the aircraft.

公开(公告)号：US10343778B2

公开(公告)日：2019-07-09

申请号：US15160251

申请日：2016-05-20

Applicant: DASSAULT AVIATION

Inventor： Denis Peuziat

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

Abstract: A retractable support for a screen, and interior layout assembly for an aircraft cabin comprising such a support are provided. The retractable support for a screen includes a housing for receiving the screen in a retracted position, and an arm movably mounted relatively to the housing between a retracted position inside the housing and a deployed position outside the housing. The arm includes first and second rigid segments jointed with each other so that the second segment pivots relatively to the first segment around a first pivot axis between a compact configuration, in which the second segment is fitted into a recess of the first segment, and an extended configuration, in which the second segment extends out of said recess.

公开(公告)号：USD850884S1

公开(公告)日：2019-06-11

申请号：US29603958

申请日：2017-05-15

Applicant: DASSAULT AVIATION

Designer： Matthieu Poidatz ,  Agnès Gervais

公开(公告)号：US20190164438A1

公开(公告)日：2019-05-30

申请号：US16198991

申请日：2018-11-23

Applicant: DASSAULT AVIATION

Inventor： Cyrille GRIMALD

IPC: G08G5/00

Abstract: An aircraft mission computing system includes a computing engine for computing aircraft trajectories during a mission that comprises a trajectory computing module capable of computing a mission trajectory between the geographical point of origin and the geographical destination point as a function of the airplane performance and operational mission specifications. The trajectory computing module is configured to compute at least one iso-movement curve of the aircraft, in particular at least one isochronous curve and/or at least one fuel iso-consumption curve from at least one point of the trajectory and is able to determine at least one other point of the trajectory on the iso-movement curve of the aircraft.

公开(公告)号：US20190118940A1

公开(公告)日：2019-04-25

申请号：US16168801

申请日：2018-10-23

Applicant: DASSAULT AVIATION

Inventor： François DUPRE ,  Olivier MORELLEC ,  Julien PRODIGUE ,  Olivier CANTINAUD

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

Abstract: A system for controlling a lateral trajectory of an aircraft includes a rudder bar. Each pedal of the rudder bar is movable between a neutral position (pn) and an end-of-travel position (pf) along a unique travel. A movement of the pedal between the neutral position (pn) and an activation position (pact) commands a lateral movement by actuating a lateral movement device of a first set including a nose gear wheel, the different braking of the aircraft being nonactive. A movement of the pedal from the activation position (pact) to the end-of-travel position (pf) commands a lateral movement by actuating a device of the first set and the differential braking. A haptic feedback generator applies a first haptic profile to each pedal between the neutral position (pn) and the activation position (pact) and a second haptic profile from the activation position (pact) toward the end-of-travel position (pf).

公开(公告)号：US10209710B2

公开(公告)日：2019-02-19

申请号：US15063940

申请日：2016-03-08

Applicant: DASSAULT AVIATION

Inventor： Sébastien Lepage

IPC: G05D1/00 ,  G05D1/08 ,  B64D31/08 ,  B64C19/02 ,  B64C13/02 ,  B64C13/16 ,  G01C23/00

Abstract: A piloting assistance system for an aircraft during manual piloting is provided. The piloting assistance system includes a monitoring module, configured to compare an acceleration of the aircraft to an authorized acceleration that depends on a speed of the aircraft, an acceleration control module, able to be switched between an activated state and a deactivated state, and configured so as, in the activated state, excluding the deactivated state, to generate a control signal of at least one control device of the acceleration of the aircraft to push the acceleration of the aircraft toward the authorized acceleration range, in order to keep or push the speed of the aircraft in a predefined usage speed range, the monitoring module being configured to activate the acceleration control module when the acceleration of the aircraft is not comprised in the authorized acceleration range.

公开(公告)号：US10109202B2

公开(公告)日：2018-10-23

申请号：US15063444

申请日：2016-03-07

Applicant: DASSAULT AVIATION

Inventor： Eric Boulle ,  Jean-Philipe Roue

IPC: G08G5/00 ,  G08G5/02 ,  G05D1/10 ,  G05D1/04 ,  G05D1/06

Abstract: A method and system for determining in real time a vertical trajectory of an aircraft is provided. The method includes a step for providing an initial vertical trajectory comprising an initial phase for changing flight level according to a first slope, between a first point at a first altitude, and a second point at a second altitude, at least one step for modifying the vertical trajectory, comprising a phase for detecting a triggering element when the aircraft is at the first altitude, when said triggering element is detected, and a phase for determining a modified vertical trajectory, said modified vertical trajectory comprising a modified phase for changing flight level according to a second predefined slope, from a modified point at said first altitude, distinct from said first point, to said second altitude.

公开(公告)号：US20180265218A1

公开(公告)日：2018-09-20

申请号：US15915703

申请日：2018-03-08

Applicant: DASSAULT AVIATION

Inventor： Florent RIMBAUD ,  Frank RENAUD

IPC: B64D45/04

CPC classification number: B64D45/04 ,  G01C5/005 ,  G05D1/0646 ,  G08G5/0021 ,  G08G5/0086 ,  G08G5/045

Abstract: A ground proximity warning system for an aircraft includes a plurality of alarm generators, each able to generate an alarm by verifying evolution conditions of the aircraft specific to each alarm generator, the verification using data obtained from at least one measuring sensor of the aircraft. The ground proximity warning system includes a unit for selective deactivation of at least some of the alarm generators, able to be implemented during a search and rescue mission carried out by the aircraft, and an auxiliary alarm generator, capable of emitting a ground proximity alarm based on the safety height chosen for the search and rescue mission, when the selective deactivation unit is implemented.

公开(公告)号：US20180259357A1

公开(公告)日：2018-09-13

申请号：US15915731

申请日：2018-03-08

Applicant: DASSAULT AVIATION

Inventor： Frank RENAUD ,  Christian PAQUIER

IPC: G01C23/00 ,  B64D43/00

CPC classification number: G01C23/005 ,  B63C9/01 ,  B64D43/00 ,  G05D1/0202 ,  G08G5/0013 ,  G08G5/0034 ,  G08G5/006

Abstract: An assembly for implementing an aircraft trajectory includes a flight management system including a viewer, and a display application, on the viewer, for navigation data of the aircraft including waypoints of the aircraft along a trajectory. The flight management system includes an application for recovering tactical track monitoring data, the display application being able to display, dynamically on the viewer, a tactical track positioning symbol corresponding to the or each tactical track being monitored, the position of the positioning symbol being updated by the display application as a function of position data of the aircraft and tactical track monitoring data corresponding to the tactical track, received from a data acquisition apparatus, via a data transmission system.

公开(公告)号：US20170267327A1

公开(公告)日：2017-09-21

申请号：US15458710

申请日：2017-03-14

Applicant: DASSAULT AVIATION

Inventor： Pascal HERAU ,  Guillaume DEDIEU

IPC: B64C1/14

CPC classification number: B64C1/1407 ,  B64C1/14 ,  B64C1/1415 ,  B64C1/1423 ,  B64C1/143 ,  E05Y2900/502 ,  F16D3/207 ,  F16D11/14 ,  F16D63/006

Abstract: A connecting mechanism between an aircraft door and a structure of the aircraft, a related aircraft and method are provided. The connecting mechanism includes an arm intended to be hinged on to the structure, a rotating connection between the door and the arm. The rotating connection may be disengaged from a connection configuration for connecting the door with the arm in an open position of the door, into an uncoupling configuration for uncoupling of the door from the arm, in a closed door position of the door.