公开(公告)号：WO2008025931A2

公开(公告)日：2008-03-06

申请号：PCT/FR2007/051861

申请日：2007-08-31

Applicant: DASSAULT AVIATION ,  LE PEUVEDIC, Jean-Marc ,  PETIT, Anne-Sophie

Inventor： LE PEUVEDIC, Jean-Marc ,  PETIT, Anne-Sophie

IPC: B64D43/00 ,  G01P13/02

CPC classification number: G01P5/16 ,  G01P13/025

Abstract: Dispositif (100), notamment pour positionner un mobile (101) dans un fluide, caractérisé en ce qu'il comprend : - un ensemble d'au moins deux sondes (1) disposées chacune en un point de mesure différent, et équipée chacune d'un capteur (3) de pression différentielle, - des moyens pour fournir une contre-pression (P7) commune à tous les capteurs dudit l'ensemble, - des moyens calcul comprenant des moyens (20) pour calculer une pression différentielle utile (DP) à partir des pressions différentielles (DPA, DPB) respectives mesurées par chaque capteur (3A,3B) respectif d'une paire de sondes (1A,1B) parmi les sondes dudit ensemble. Un tel dispositif est particulièrement adapté pour être utilisé dans un avion.

Abstract translation: 装置（100），特别是用于将流动的车辆（101）定位在流体中，其特征在于，它包括：一组至少两个探针（1），每个探针具有不同的测量点，并且每个探针具有传感器 （3）的压差 - 用于向所述组合计算装置的所有传感器提供接合背压（P7）的装置，包括装置（20），用于从相应的压差（DPA，DPB）计算有用的压差 ）由所述组件的探针中的每对传感器（1A，1B）由每对传感器（3A，3B）测量。 这种装置特别适用于飞机。

公开(公告)号：WO2006059051A1

公开(公告)日：2006-06-08

申请号：PCT/FR2005/051031

申请日：2005-12-02

Applicant: EADS CCR ,  EUROPEAN AERONAUTIC DEFENCE AND SPACE COMPANY EADS FRANCE ,  DASSAULT AVIATION ,  EUROCOPTER ,  SOCCARD, Eric

Inventor： SOCCARD, Eric

IPC: B29C70/38 ,  B29C35/02

CPC classification number: B29C70/386 ,  B29C35/0288 ,  B29C35/08 ,  B29C65/1654 ,  B29C65/1661 ,  B29C65/1664 ,  B29C65/1667 ,  B29C65/1674 ,  B29C65/1696 ,  B29C66/001 ,  B29C66/00141 ,  B29C66/1122 ,  B29C66/45 ,  B29C66/721 ,  B29C66/7392 ,  B29C66/7394 ,  B29C66/81457 ,  B29C66/8161 ,  B29C66/8362 ,  B29C66/91216 ,  B29C66/91231 ,  B29C66/9161 ,  B29C66/962 ,  B29K2105/06

Abstract: Le système de drapage de bandes de matériau composite (3) comprend, outre une tête de déroulement (20), un ensemble original composé d'une source lumineuse (4) pour échauffer la bande (3) et durcir le composite et une paire de rouleaux (6a et 6b) appliquant la pression voulue pour assembler la bande à un stratifié (2) déjà déposé ou l'appliquer sur le support (1). Comme l'application de chaleur est concentrée à distance des rouleaux (6a et 6b) et avec une incidence perpendiculaire, ceux-ci peuvent être construits en matière élastique sans inconvénient, ce qui leur permet de bien s'adapter à la courbure transversale de l'outillage (1) de support et d'appliquer une pression uniforme.

Abstract translation: 本发明涉及一种用于复合材料（3）的带状盖布的系统，包括：退绕头（20），包括用于加热带（3）的光源（4）的原始组件和 硬化复合材料，以及一对施加期望压力以便将带与预沉积的层压板（2）组装或将其施加到支撑件（1）上的辊（6a和6b）。 由于施加热量集中在与辊（6a和6b）一定距离并且与其正常入射的情况下，所述辊可以方便地由弹性材料制成。 结果，辊可以很好地适应支撑工具（1）的交叉曲率并施加均匀的压力。

公开(公告)号：WO1994023989A2

公开(公告)日：1994-10-27

申请号：PCT/FR1994000404

申请日：1994-04-12

Applicant: DASSAULT AVIATION ,  ARCHITECTURE NAVALE MVPVLP ,  SOURNAT, André ,  DE BERGH, Alain ,  THEBAULT, Alain ,  PERRIER, Philippe ,  LAURIOT-PREVOST, Vincent ,  VAN PETEGHEM, Marc

Inventor： DASSAULT AVIATION ,  ARCHITECTURE NAVALE MVPVLP

IPC: B63B01/24

CPC classification number: B63B1/28 ,  B63B1/14

Abstract: A wind-propelled hydrofoil comprising a forward assembly with at least partially submerged forward foils and a fully submerged aft foil. The forward foils (43, 44) are such that the resultant of the vertical forces drops when said assembly is translated vertically upwards, with a heave characteristic (F), and increases when said forward assembly is subject to upward pitching, with an incidence characteristic (A). The aft foil (46) has an incidence characteristic (R) such that R(d-g) - Ag + F(g +r ) > 0, wherein d is the distance between the aft foil (46) and the centre of heave, g is the distance between the centre of gravity and the centre of heave, and r is the gyration radius of the hydrofoil.

Abstract translation: 包括具有至少部分浸没的前箔的前组件和完全浸没的后箔的风力推进水翼。 正向箔（43,44）使得当所述组件垂直向上平移时具有起伏特性（F），垂直力的结果将下降，并且当所述前部组件经受向上倾斜时增加，具有入射特性 （一个）。 后箔（46）具有使得R（dg）-Gg + F（g 2 + r 2）> 0的入射特性（R），其中d是后箔（46）和 重心的中心，g是重心和起伏中心之间的距离，r是水翼的回转半径。

公开(公告)号：JP3753266B2

公开(公告)日：2006-03-08

申请号：JP27647996

申请日：1996-10-18

Applicant: ダソール−アヴィアシオンDassault−Aviation

Inventor： ペリエ、フィリップ

IPC: B64F1/06

CPC classification number: B64F1/06

公开(公告)号：USD1059864S1

公开(公告)日：2025-02-04

申请号：US29832218

申请日：2022-03-25

Applicant: DASSAULT AVIATION

Designer： Adrian Jimenez ,  Quentin Dugas

公开(公告)号：US12067811B2

公开(公告)日：2024-08-20

申请号：US17574644

申请日：2022-01-13

Applicant: DASSAULT AVIATION

Inventor： Patrick Dignimont ,  Jérôme Cappelle ,  Serge Bruillot

IPC: G07C5/00 ,  B64D45/00 ,  B64D47/00 ,  G07C5/08

CPC classification number: G07C5/008 ,  B64D45/00 ,  B64D47/00 ,  G07C5/0841 ,  B64D2045/0085

Abstract: A system for secure transfer of digital aircraft data comprising redundant data producer systems includes a first data producer, capable of producing first data, at successive moments, and a second data producer, redundant to the first system. The second data producer is capable of producing an integrity check result relating at least to second data which it produces in a manner redundant to the first data, the integrity check result being transmitted to a data consumer. The data consumer is capable of retrieving the first data and the integrity check result produced by the second system, to produce a new integrity check result from the first data and compare the new integrity check result with the integrity check result produced by the second system.

公开(公告)号：US20240109648A1

公开(公告)日：2024-04-04

申请号：US18373276

申请日：2023-09-27

Applicant: DASSAULT AVIATION

Inventor： Xavier BERNARD ,  Zdenek JOHAN ,  Aurélien MERLET

IPC: B64C23/06 ,  B64C1/26

CPC classification number: B64C23/06 ,  B64C1/26

Abstract: An aircraft portion with reduced drag includes a wing-fuselage junction fairing at the interface between the wing and the fuselage. The junction fairing has an outer surface including two lateral portions each covering the root of a respective wing, and a lower portion connecting the side portions to each other and extending under the fuselage. The flow of air around the junction fairing during the movement of the aircraft generates at least two vortices induced on both sides, respectively, of a median longitudinal plane. The aircraft portion also includes at least two vortex generating devices extending from the lower portion of the outer surface of the junction fairing on both sides, respectively, of the median longitudinal plane.

公开(公告)号：US11884379B2

公开(公告)日：2024-01-30

申请号：US17724653

申请日：2022-04-20

Applicant: DASSAULT AVIATION

Inventor： Jérôme Le Borloch ,  François Pineau

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

CPC classification number: B64C13/042 ,  G05G1/015 ,  G05G1/04 ,  G05G5/005 ,  G05G5/05 ,  G05G2505/00

Abstract: 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：US11851183B2

公开(公告)日：2023-12-26

申请号：US17077684

申请日：2020-10-22

Applicant: DASSAULT AVIATION

Inventor： Lionel Patrick Germe ,  Emmanuel Picut ,  Alain Levavasseur ,  Erwan Boulo ,  Jérémie Guerard

IPC: B64D11/06 ,  B64D41/00

CPC classification number: B64D11/0621 ,  B64D11/0601 ,  B64D11/0605 ,  B64D11/0638 ,  B64D41/00 ,  B64D2201/00

Abstract: An aircraft cabin includes at least one seat able to receive at least one passenger; at least one table arranged opposite the seat; and a safety device able to be mounted on the table, below the table or received in the table. The safety device includes a deployable protection assembly including an airbag deployable from a retracted idle configuration to a deployed safety configuration, and a system for controlling the deployment of the or each airbag, able to trigger the deployment of the airbag beyond a threshold deceleration value of the aircraft.

公开(公告)号：US20230278699A1

公开(公告)日：2023-09-07

申请号：US18118129

申请日：2023-03-06

Applicant: DASSAULT AVIATION

Inventor： Laurent PISTIAUX ,  Vincent MATEUS

IPC: B64C13/04

CPC classification number: B64C13/044 ,  B64C25/42

Abstract: An aircraft rudder pedal includes a frame, a pair of pedals, an output shaft and a mechanical kinematic chain for transmitting to the output shaft a displacement of at least one of the pedals relative to the frame. The mechanical kinematic chain comprises a central transmission part able to be rotated relative to the frame by a displacement of one of the pedals relative to the frame. The mechanical kinematic chain also includes a transmission mechanism joining the central transmission part to the output shaft. The transmission mechanism includes a homokinetic association of two universal joints between said central transmission part and the output shaft.