公开(公告)号：US20140097973A1

公开(公告)日：2014-04-10

申请号：US14044305

申请日：2013-10-02

Applicant: DASSAULT AVIATION

Inventor： Olivier BAUDSON ,  Arnaud TURPIN

IPC: G08G5/00

CPC classification number: G08G5/0047 ,  G01C23/00 ,  G06T19/006

Abstract: The system according to the invention comprises an assembly for managing the graphic interface of a display, capable of controlling the display, on at least a first region of the display, of a peripheral area formed by a synthetic image comprising at least one synthetic surface representation of the terrain, and capable of maintaining at least one area representative of the position of a landing runway, centered on the landing runway, and at least one front area, adjacent to the center area, substantially free of any synthetic surface representation of the terrain. The management assembly includes means for dynamically defining the length (L) of the front area on the display as a function of a vertical decision position (DP) associated with a selected approach for said landing runway.

Abstract translation: 根据本发明的系统包括用于管理显示器的图形界面的组件，其能够在显示器的至少第一区域上控制由包括至少一个合成表面表示的合成图像形成的外围区域的显示器 并且能够保持代表在着陆跑道上的着陆跑道的位置的至少一个区域，以及与中心区域相邻的至少一个前区域，基本上没有地形的任何合成表面表示 。 管理组件包括用于根据与所述着陆跑道的所选方法相关联的垂直决定位置（DP）来动态地定义显示器上的前区域的长度（L）的装置。

公开(公告)号：US20140097295A1

公开(公告)日：2014-04-10

申请号：US14044110

申请日：2013-10-02

Applicant: DASSAULT AVIATION

Inventor： Fabien BOUFFANAIS ,  Benoit DE MAQUEVILLE ,  Olivier GAVOUYERE ,  Zdenek JOHAN

IPC: B64C1/14

CPC classification number: B64C1/1484 ,  B64C1/1492 ,  B64D47/08

Abstract: The nose section for a flying machine according to the invention comprises an enclosure delimiting a nose cone extending along a longitudinal axis (A-A′), the enclosure delimiting a window, and a glass closing the window extending transversely relative to the longitudinal axis (A-A′). The nose section includes an optical sensor, in particular a camera, positioned in the enclosure behind the glass. The enclosure defines a recess, the window covered by the glass being at least partially positioned in the recess.

Abstract translation: 根据本发明的用于飞行机器的鼻部部分包括限定沿着纵向轴线（AA'）延伸的鼻锥的外壳，限定窗口的外壳和关闭相对于纵向轴线（AA'）横向延伸的窗口的玻璃， ）。 鼻部包括位于玻璃后面的外壳中的光学传感器，特别是相机。 外壳限定凹部，由玻璃覆盖的窗口至少部分地定位在凹部中。

公开(公告)号：US20140002107A9

公开(公告)日：2014-01-02

申请号：US13691354

申请日：2012-11-30

Applicant: DASSAULT AVIATION

Inventor： Gerard Leflour

IPC: G01N22/00

CPC classification number: G01N22/00 ,  G01N22/02 ,  G01R27/32

Abstract: The device according to the invention comprises a holder and a transmitter supported by the holder, the transmitter being capable of transmitting an electromagnetic signal toward the surface any transmission frequency (Fe). It includes a receiver for receiving a signal reflected on the surface. The device comprises a guide assembly for guiding the movement of the holder to move the transmitter and the receiver across from the surface, tangentially relative to the surface. It comprises an extraction unit for extracting, in the signal received by the receiver, a shifted frequency component of the transmission frequency resulting from a local impedance variation of the surface. The extraction unit produces an extracted signal representative of the state of the surface from the shifted frequency component.

Abstract translation: 根据本发明的装置包括保持器和由保持器支撑的发射器，所述发射器能够向所述表面传输电磁信号任何传输频率（Fe）。 它包括用于接收在表面上反射的信号的接收器。 该装置包括用于引导保持器的运动的引导组件，以使发射器和接收器相对于表面相对于表面移动。 它包括提取单元，用于在由接收器接收的信号中提取由表面的局部阻抗变化产生的传输频率的移位频率分量。 提取单元从移位的频率分量产生表示表面状态的提取信号。

公开(公告)号：US12252236B2

公开(公告)日：2025-03-18

申请号：US17574677

申请日：2022-01-13

Applicant: DASSAULT AVIATION

Inventor： Jérôme Cappelle ,  François Pineau ,  William Faysse

IPC: B64C13/50 ,  B64D31/04 ,  B64D31/06

Abstract: A system for piloting an aircraft includes a throttle, a flight parameter sensor system, and an engine calculator controlling thrust parameters of an engine of the aircraft. The piloting system includes a flight control unit connected to the engine calculator, the sensors and the throttle. The flight control unit generates a thrust control vector from a flight control law and sends a digital signal including the generated thrust control vector to the engine calculator. The engine calculator controlling said thrust parameters of the engine depending on the generated thrust control vector received.

公开(公告)号：US12084191B2

公开(公告)日：2024-09-10

申请号：US17724662

申请日：2022-04-20

Applicant: DASSAULT AVIATION

Inventor： Jérôme Le Borloch ,  François Pineau

IPC: B64D31/04 ,  B64C13/04 ,  G05G1/04 ,  H01H23/14

CPC classification number: B64D31/04 ,  B64C13/04 ,  B64C13/042 ,  G05G1/04 ,  G05G2505/00 ,  H01H23/145

Abstract: 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：US11945570B2

公开(公告)日：2024-04-02

申请号：US17550006

申请日：2021-12-14

Applicant: DASSAULT AVIATION

Inventor： Fabien Cockenpot ,  François Pineau ,  Jérôme Le Borloch

IPC: B64C13/04 ,  B64C13/06 ,  B64C13/12

CPC classification number: B64C13/0421 ,  B64C13/06 ,  B64C13/12

Abstract: A piloting device for piloting an aircraft comprises a first and a second control stick mounted movable on a support. The device comprises a priority selection module configured to switch the first and second control sticks between a piloting configuration and a non-piloting configuration. The device further comprises a detection system for detecting the positions of the first and second control sticks; a first and second actuation system configured to generate respective first and second forces on the respective first and second control stick; and a control module configured to control the actuation system of the control stick which is in a non-piloting configuration such that the positions of the control sticks are identical.

公开(公告)号：US11661210B2

公开(公告)日：2023-05-30

申请号：US16583445

申请日：2019-09-26

Applicant: DASSAULT AVIATION

Inventor： François-Xavier D'Arbonneau

IPC: B64F5/60 ,  B64C19/00 ,  G01C9/00

CPC classification number: B64F5/60 ,  B64C19/00 ,  G01C9/005

Abstract: A method is for detecting a blockage of a wind vane (12) of an aircraft, with the wind vane (12) including a support (20), a paddle (22) mounted rotating relative to the support (20) along an axis (A), a motor (28) able to exert a rotational torque on the paddle (22) along the axis (A), the motor (28) being connected to a processing unit (18). The method includes applying a predetermined blockage detection torque on the paddle (22) by the motor (28); measuring at least one piece of information representative of a resistance of the paddle (22) to the predetermined detection torque; and generating, via the processing unit (18), a blocking information signal, if a predetermined condition based on the representative information is verified.

公开(公告)号：US11436928B2

公开(公告)日：2022-09-06

申请号：US16821779

申请日：2020-03-17

Applicant: DASSAULT AVIATION

Inventor： Cyrille Grimald ,  Benoit Urien

IPC: G08G5/00 ,  G06F16/29 ,  B64D45/00 ,  G05D1/04

Abstract: Aircraft mission calculation system includes a first calculator configured to calculate a plurality of iso-displacement curves from a selected point, at a displacement range corresponding to several successive displacement increments of the aircraft from the selected point, the iso-displacement curves being obtained at the displacement range for a displacement of the aircraft to a given flight level from displacements of the aircraft at distinct flight altitude levels. The first calculator is configured to determine, based on iso-displacement curves up to the given flight level, obtained at distinct flight altitude levels, taken at the same displacement range of the aircraft, an extended iso-displacement curve at the given flight level maximizing the displacement of the aircraft from the geographical point of origin or minimizing the displacement of the aircraft toward the geographical destination point.

公开(公告)号：US11358735B2

公开(公告)日：2022-06-14

申请号：US15915703

申请日：2018-03-08

Applicant: DASSAULT AVIATION

Inventor： Florent Rimbaud ,  Frank Renaud

IPC: B64D45/04 ,  G08G5/04 ,  G08G5/00 ,  G05D1/06 ,  G01C5/00

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：US20220119117A1

公开(公告)日：2022-04-21

申请号：US17500028

申请日：2021-10-13

Applicant: DASSAULT AVIATION

Inventor： Quentin DUGAS ,  Jean-Rémi BILLON

IPC: B64D11/06

Abstract: An interior layout of an aircraft cabin extends along a longitudinal axis on a floor and comprises a table having at least one leg, at least one base for each leg and at least one flat tabletop. Each base is intended to be fixed to the floor, each leg is mounted on a base, and each flat tabletop is mounted on at least one leg. The table defines at least one main aisle accessible to a passenger of the aircraft. The main aisle extends in the longitudinal axis along a longitudinal edge of the flat tabletop. The interior layout comprises at least one seat arranged opposite the table. The seat has a seating direction oriented transversely to the longitudinal axis.