公开(公告)号：US20240321125A1

公开(公告)日：2024-09-26

申请号：US18608913

申请日：2024-03-18

申请人： DASSAULT AVIATION

发明人： Stéphane PICAUT ,  Yann COUREAUD

IPC分类号： G08G5/02 ,  G08G5/00

CPC分类号： G08G5/025 ,  G08G5/0021 ,  G08G5/0047

摘要： A method for assisting an aircraft in landing on a runway and an associated system includes determining a target exit point from the runway and a target taxi speed at which the aircraft has to take the target exit; calculating a target ground distance representative of a ground deceleration phase; and calculating the position of a target touchdown point on the basis of the target ground distance. The target ground distance is calculated as a function of a target deceleration profile for the aircraft to reach the target exit point at the target taxi speed.

公开(公告)号：US12084192B2

公开(公告)日：2024-09-10

申请号：US17872628

申请日：2022-07-25

申请人： DASSAULT AVIATION

发明人： Angélique Beaucamp ,  Laurent Fillet ,  Nicolas Le Corre

IPC分类号： B64D31/04 ,  G05D1/00

CPC分类号： B64D31/04 ,  G05D1/0083

摘要： A device is for assisting the piloting in acceleration of an aircraft in taking in order to control its speed. The comprises a control member, adapted to be actuated by a pilot from a neutral position to define a taxiing piloting command for controlling the speed of the aircraft and a central controller, adapted to operate pilot at least one engine of the aircraft to apply the taxiing command defined by the pilot. The taxiing piloting command is an acceleration or deceleration command of the aircraft during taxiing.

公开(公告)号：USD1029343S1

公开(公告)日：2024-05-28

申请号：US29831069

申请日：2022-03-17

申请人： DASSAULT AVIATION

设计人： Ludovic Hamon ,  Adrian Jimenez

摘要： FIG. 1 is a downward facing perspective view of a lamp, showing the present invention;
FIG. 2 is a front elevation view of the lamp of the present invention;
FIG. 3 is a rear elevation view of the lamp of the present invention;
FIG. 4 is a top plan view of the lamp of the present invention;
FIG. 5 is a bottom plan view of the lamp of the present invention;
FIG. 6 is a right side elevation view of the lamp of the present invention;
FIG. 7 is a left side elevation view of the lamp of the present invention; and,
FIG. 8 is a top portion of a downward facing perspective view of the selected portion 8 in FIG. 1.
The broken line representations in the figures depict portions of the article that form no part of the claimed design.

公开(公告)号：US11857324B2

公开(公告)日：2024-01-02

申请号：US17676128

申请日：2022-02-19

申请人： DASSAULT AVIATION

发明人： François Salmon-Legagneur ,  Valentin Ligier ,  Cyril Saint Requier

IPC分类号： G08B23/00 ,  A61B5/18 ,  A61B5/00

CPC分类号： A61B5/18 ,  A61B5/742 ,  A61B5/746 ,  A61B5/7475

摘要： A system for monitoring the operational status of an aircraft crew includes a unit for determining at least one pilot state based on first monitoring data of a high design assurance level and second monitoring data of a lower design assurance level. The determination unit includes a first evaluation module capable of obtaining a high-level pilot state from the first data, regardless of the second data; a second evaluation module capable of determining a low-level pilot state, from at least the second data; and a consolidation module for determining a consolidated pilot state. The consolidated pilot state is obtained as a function of the high-level pilot state and the low-level pilot state.

公开(公告)号：US20230286670A1

公开(公告)日：2023-09-14

申请号：US18118396

申请日：2023-03-07

申请人： DASSAULT AVIATION

发明人： Sébastien LEPAGE ,  Arnaud TURPIN

IPC分类号： B64D45/08

CPC分类号： B64D45/08

摘要： An aircraft display system includes a display; and a unit for generating display on the display, suitable for dynamically displaying on the display at least one horizon line, a slope scale with respect to the horizon line, and a velocity vector symbol. When approaching a landing strip, the display generating unit is suitable for displaying, below the horizon line, a flare floor symbol, defining, along with the horizon line, a range of possible slope values for the flare.

公开(公告)号：US11668127B2

公开(公告)日：2023-06-06

申请号：US17077518

申请日：2020-10-22

申请人： DASSAULT AVIATION

发明人： Patrick Chambers

IPC分类号： B64C1/14 ,  E05D15/56 ,  E05D15/20 ,  B64D11/00 ,  E05D15/24

CPC分类号： E05D15/20 ,  B64C1/1407 ,  B64C1/1415 ,  B64D11/003 ,  E05D15/248 ,  E05D15/56 ,  E05Y2900/502

摘要： 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.

公开(公告)号：US11495133B2

公开(公告)日：2022-11-08

申请号：US16821361

申请日：2020-03-17

申请人： DASSAULT AVIATION

发明人： Gérard Leflour ,  Jérôme Lagarde ,  Paul Soudais ,  Nicolas Moulin

IPC分类号： G08G5/00 ,  G01C23/00 ,  B64D45/08 ,  H01Q1/28

摘要： An aircraft enhanced vision system includes an electromagnetic sensor comprising at least one group of transmitters and at least one group of receivers. The electromagnetic sensor includes a waveform generation assembly powering each transmitter in order to generate the transmitted signal and a signal capture assembly to capture the signal received by each receiver after reflection off of the ground. The transmitters are distinct and spaced apart from the receivers, being arranged so as to form at least one virtual transmitter/receiver network extending in an elongation direction perpendicular to the observation direction from each transmitter/receiver combination between the group of transmitters and the group of receivers.

公开(公告)号：US20220340294A1

公开(公告)日：2022-10-27

申请号：US17724662

申请日：2022-04-20

申请人： DASSAULT AVIATION

发明人： Jérôme LE BORLOCH ,  François PINEAU

IPC分类号： B64D31/04 ,  G05G5/00 ,  G05G5/05 ,  G05G1/02

摘要： A command device for controlling a mechanical energy reduction assembly of an aircraft, movable between an inactive configuration and a maximum mechanical energy reduction configuration, includes a rocker button, movable between a mechanical energy reduction assembly configuration maintaining position, a first position of incremental movement of the mechanical energy reduction assembly to its maximum mechanical energy reduction configuration and a second position of incremental movement of the mechanical energy reduction assembly to its inactive configuration. The command device further includes at least one return element configured to return the rocker button to its maintaining position.

公开(公告)号：US20220340261A1

公开(公告)日：2022-10-27

申请号：US17724653

申请日：2022-04-20

申请人： DASSAULT AVIATION

发明人： Jérôme LE BORLOCH ,  François PINEAU

IPC分类号： B64C13/04 ,  G05G1/015 ,  G05G5/05 ,  G05G1/04 ,  G05G5/00

摘要： A control system is for a high lift assembly of an aircraft. The assembly is controllable in two aerodynamic configurations each with different lift. The control system includes a manual control device operable by a pilot of the aircraft. The manual control device includes at least one member movable relative to a base body. The movable member can be moved relative to the base body between a rest position, a first position and a second distinct position. The manual control device includes a resilient return device for the movable member in the rest position. The manual control device issues a signal when the movable member reaches either the first or second position, to move the high lift assembly between two of the aerodynamic configurations.

公开(公告)号：US20220223051A1

公开(公告)日：2022-07-14

申请号：US17574659

申请日：2022-01-13

申请人： DASSAULT AVIATION

发明人： Serge BRUILLOT ,  Patrick DIGNIMONT ,  Jérôme CAPPELLE

IPC分类号： G08G5/00 ,  B64D45/00 ,  H04W74/00 ,  H04W12/06 ,  H04W76/11

摘要： A secure transfer system for digital aircraft data includes a data producer system configured to generate a data capsule at each data production and a data consumer system. The consumer system is configured to retrieve each capsule to extract an identifier, a refresh indicator, a functional data packet, and an integrity control result. It is configured to check the integrity of the data in the capsule by establishing a new integrity check result from the identifier, the refresh indicator, and the functional data packet retrieved from the capsule and comparing the new integrity check result to the integrity check result of the capsule. The data capsule is in an integrity state when the new integrity check result matches the integrity check result retrieved from the capsule.