公开(公告)号：US20220265187A1

公开(公告)日：2022-08-25

申请号：US17676128

申请日：2022-02-19

Applicant: DASSAULT AVIATION

Inventor： François SALMON-LEGAGNEUR ,  Valentin LIGIER ,  Cyril SAINT REQUIER

IPC: A61B5/18 ,  A61B5/00

Abstract: A system for monitoring the operational status of an aircraft crew comprises 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 comprises 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：US20220185454A1

公开(公告)日：2022-06-16

申请号：US17549992

申请日：2021-12-14

Applicant: DASSAULT AVIATION

Inventor： Jérôme LE BORLOCH

IPC: B64C13/04 ,  B64C13/12

Abstract: A piloting device for piloting an aircraft includes a first and a second control stick movably mounted on a support, a detection system for detecting the positions of the first and second control sticks, an elastic mechanism configured to apply a restoring force to the second control stick, first and second actuation systems configured to apply respective first and second position adjustment forces to the respective first and second control sticks, and a control module configured to control the second adjustment force so that the positions of the first and second control sticks are identical. The control module is configured to control the first adjustment force based on the second adjustment force and the restoring force.

公开(公告)号：US11325721B2

公开(公告)日：2022-05-10

申请号：US16929801

申请日：2020-07-15

Applicant: DASSAULT AVIATION

Inventor： Carole Andre

IPC: B01D53/22 ,  B64D37/32 ,  B01D69/04 ,  B01D69/08 ,  B64D37/02

Abstract: An inerting system comprises an air separating device having an enclosure (40) having at least one air inlet (46) and one outlet (48) for oxygen-depleted air. The air separating device (18) is configured to generate, from an air inlet flow coming from the air inlet (46) of the enclosure (40), an outlet flow of oxygen-depleted air and to discharge the outlet flow of oxygen-depleted air through the outlet (48) for oxygen-depleted air. The inerting system (14) comprises a heating system (20), outside the enclosure (40), configured to heat at least one region of the enclosure (40).

公开(公告)号：US11267552B2

公开(公告)日：2022-03-08

申请号：US16261486

申请日：2019-01-29

Applicant: DASSAULT AVIATION

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

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

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：US11124315B2

公开(公告)日：2021-09-21

申请号：US16009798

申请日：2018-06-15

Applicant: DASSAULT AVIATION

Inventor： Fabrice Tristant

IPC: B64D45/02 ,  B64C1/36 ,  H01Q1/28 ,  H02G13/00

Abstract: A lightning protection system of an aircraft includes a wall defining an inner surface and an outer surface. The outer surface is configured to come into contact with a mass of air located around the aircraft. The lighting protection system also includes at least two electrically conductive lighting traps received in holes traversing the wall and at least one strip with pellets having an electrically insulating substrate and electrically conductive pellets spaced apart from one another on the electrically insulating substrate. The strip with pellets is fastened on the wall by the two lightning traps. The strip with pellets is attached on the inner surface of the wall.

公开(公告)号：US20210253275A1

公开(公告)日：2021-08-19

申请号：US17175905

申请日：2021-02-15

Applicant: DASSAULT AVIATION

Inventor： Virginie MARCELOT ,  Rémi BREBAN

IPC: B64F5/60 ,  B64D43/00 ,  B64D45/00 ,  G07C5/08

Abstract: A system for monitoring the operational status of an aircraft between successive missions of the aircraft includes a computer able to determine at least one operational impact measurement on at least one future mission of the aircraft related to the aircraft and/or to an aircraft equipment and/or to a consumable and/or to the aircraft crew, the operational impact measurement being determined as a function of the flight logbook and/or technical logbook data of at least one already completed mission of the aircraft and/or a context of the future mission. The system includes a display and a display manager on the display, able to display on the display at least one operational impact indicator related to the aircraft and/or to the equipment and/or to the consumable and/or to the crew, as a function of the operational impact measurement determined by the computer.

公开(公告)号：US10513348B2

公开(公告)日：2019-12-24

申请号：US15582811

申请日：2017-05-01

Applicant: DASSAULT AVIATION

Inventor： Jérôme Tabuteau ,  Jérôme Brunet

IPC: B64D47/00 ,  B64C1/36 ,  B64D45/00 ,  H01Q1/28 ,  H01Q1/12 ,  H01Q1/42 ,  H01Q3/06

Abstract: A support device for a radio equipment of an aircraft, radio system and aircraft are provided. The support device includes a fastening structure (31), intended to be secured to a lower surface of a fuselage of an aircraft, and a support platform (33) of the radio equipment (25). The support platform (33) is mounted pivoting on the fastening structure (31) around a pivot axis (A) between an operational position and a backup position. The support device comprises a locking mechanism (56), able to be actuated from a locked configuration, in which said locking mechanism (56) keeps the support platform (33) in its operational position while preventing any pivoting of the support platform (33), to an unlocked configuration, in which the locking mechanism (56) allows the support platform (33) to pivot relative to the fastening structure (31).

公开(公告)号：US20190381760A1

公开(公告)日：2019-12-19

申请号：US16434199

申请日：2019-06-07

Applicant: DASSAULT AVIATION

Inventor： Olivier CALVO PEREZ ,  Benoit BERTON

IPC: B32B5/26

Abstract: A radome includes a laminated structure (42) in the form of a stack of composite layers (44, 46, 48, 50), each composite layer (44, 46, 48, 50) including a fibrous reinforcement mixed with an organic matrix. The composite layers includes at least one high-permittivity layer (44, 50), including a structural layer (44), and a plurality of low-permittivity layers (46, 48), including two covering layers (46, 48) sandwiching the structural layer (44) between them, each of the covering layers (46, 48) having a lower thickness to the thickness of the structural layer (44). In each low-permittivity layer (46, 48), the fibrous reinforcement includes a majority of polyolefin fibers.

公开(公告)号：US20190248467A1

公开(公告)日：2019-08-15

申请号：US16261486

申请日：2019-01-29

Applicant: DASSAULT AVIATION

Inventor： Aurélien MERLET ,  Zdenek JOHAN ,  Ximun LOYATHO ,  Gilbert ROGE

IPC: B64C3/14 ,  B64C3/32

CPC classification number: B64C3/14 ,  B64C1/26 ,  B64C3/32 ,  B64C7/00 ,  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：US10339820B2

公开(公告)日：2019-07-02

申请号：US15158807

申请日：2016-05-19

Applicant: DASSAULT AVIATION

Inventor： Arnaud Branthomme ,  Igor Fain ,  Patrick Darses

IPC: G08G5/00 ,  G01C23/00 ,  B64D43/00 ,  G06T15/20 ,  G09G5/377

Abstract: A system for displaying information related to a flight of an aircraft and an associated method are provided. The display system comprises a display device, a man-machine interface, a module for dynamically generating synthesis images, each comprising a synthetic depiction of the environment and a curve representative of a trajectory, said module being configured to generate a first synthesis image centered around a first central point of interest, to command the display thereof, and to detect an action to modify the central point of interest by an operator via said man-machine interface. The generating module is also configured to determine, as a function of said modification action, a second central point of interest, situated along said curve whatever said modification action is, to generate a second synthesis image centered around said second central point of interest, and to command the display thereof.