公开(公告)号：US09031785B2

公开(公告)日：2015-05-12

申请号：US14174728

申请日：2014-02-06

Applicant: Dassault Aviation

Inventor： Pierre Marcon

IPC: G01C21/00 ,  G01C21/12 ,  G01C21/16 ,  G01S19/49

CPC classification number: G01C21/12 ,  G01C21/165 ,  G01S19/49

Abstract: This aircraft navigation assistance system comprises an inertial navigation module adapted for providing first positional information from accelerometric and gyrometric measurements, and a module adapted for determining second positional information from satellite positioning data. The system is characterized in that it comprises means for estimating a first localization of the aircraft at a time of estimation on the basis of first positional information determined from accelerometric and gyrometric measurements at said time of estimation and second positional information determined from positioning data received prior to said time of estimation, said first localization being determined independently from any positioning data received in a time interval preceding said time of estimation, advantageously equal to a time to alert.

Abstract translation: 该飞行器导航辅助系统包括适于从加速度测量和陀螺测量提供第一位置信息的惯性导航模块，以及适于从卫星定位数据确定第二位置信息的模块。 该系统的特征在于，其包括用于基于在估计时的加速度测量和陀螺仪测量确定的第一位置信息来估计飞行器在估计时的第一定位的装置，以及从先前接收到的定位数据确定的第二位置信息 对于所述估计时间，所述第一定位独立于在所述估计时间之前的时间间隔中接收的任何定位数据独立地确定，有利地等于提醒时间。

公开(公告)号：US20150094982A1

公开(公告)日：2015-04-02

申请号：US14388778

申请日：2013-09-26

Applicant: DASSAULT AVIATION

Inventor： Sébastien Dupont De Dinechin

IPC: G01G19/07 ,  G01G19/414

CPC classification number: G01G19/07 ,  G01G19/414

Abstract: A method for determining an estimated mass of an aircraft is provided. This method includes determining a first mass of the aircraft, from characteristics of the aircraft determined before or after takeoff of the aircraft, determining, during the flight of the aircraft, a second mass of the aircraft, from a lift equation of the aircraft expressing the mass of the aircraft as a function of information representative of the load factor of the aircraft, of a lift coefficient of the aircraft, of speed information of the aircraft and of a static pressure of a mass of air passed through by the aircraft, determined from measurements by sensors of the aircraft during the flight of the aircraft, evaluating the estimated mass at said determination moment, as a function of said first and second masses.

Abstract translation: 提供了一种用于确定飞机的估计质量的方法。 该方法包括根据在飞行器起飞之前或之后确定的飞行器的特性来确定飞行器的第一质量，在飞行器飞行期间，从飞机表面的飞行器的升力方程式确定飞行器的第二飞行器质量 作为代表飞行器负载系数的信息，飞机的升力系数，飞行器的速度信息和飞行器通过的大量空气的静态压力的函数的大小，由 在飞行器飞行期间由飞行器的传感器进行的测量，作为所述第一和第二质量的函数来评估在所述确定时刻的估计质量。

公开(公告)号：US20150057960A1

公开(公告)日：2015-02-26

申请号：US14388781

申请日：2013-03-26

Applicant: DASSAULT AVIATION

Inventor： Sebastien Dupont De Dinechin

IPC: G01P21/00 ,  G01B21/00 ,  B64D43/02 ,  G01M9/06 ,  G01G23/01 ,  G01P3/80

CPC classification number: G01P21/00 ,  B64D43/02 ,  G01B21/00 ,  G01G23/01 ,  G01M9/06 ,  G01P3/806 ,  G01P5/16 ,  G01P13/025

Abstract: A method for determining a state of credibility of measurements made by sensors of an aircraft is provided. This method includes determining a speed of the aircraft, from static and total pressure measurements, determining a coefficient of lift of the aircraft from an incidence measurement and from said speed, determining a weight of the aircraft, determining if an equation of lift of the aircraft is satisfied, activating a state of optimal credibility, wherein the measurements made by said sensors are considered to be reliable if the said equation of lift is satisfied, activating a state of non-optimal credibility, wherein the measurements of at least one sensor are considered to be unreliable if the said equation of lift is not satisfied.

Abstract translation: 提供了一种用于确定由飞行器的传感器进行的测量的可信度状态的方法。 该方法包括从静态和总压力测量确定飞行器的速度，从入射测量和所述速度确定飞行器的升力系数，确定飞行器的重量，确定飞行器的升力方程 满足，激活最佳可信度的状态，其中如果所述升力等式被满足，则由所述传感器进行的测量被认为是可靠的，激活非最佳可信度的状态，其中考虑至少一个传感器的测量值 如果所述升力等式不满足则不可靠。

公开(公告)号：US20150054664A1

公开(公告)日：2015-02-26

申请号：US14388770

申请日：2013-03-26

Applicant: DASSAULT AVIATION

Inventor： Sébastien Dupont De Dinechin

IPC: G01C23/00 ,  B64D43/00

CPC classification number: G01C23/00 ,  B64D43/00

Abstract: A device for displaying flight characteristics of an aircraft is provided. The device includes a display for the selective display of flight characteristics of an aircraft, as a function of a state of credibility assigned to measurements from static pressure, total pressure and incidence sensors, configured for selectively displaying a primary set of flight characteristics comprising at least one flight characteristic coming from a measurement from one of said sensors, when the measurements from said sensors are deemed reliable, and a secondary set of flight characteristics, distinct from said primary set, comprising at least one secondary flight characteristic designed to replace a counterpart flight characteristic from the primary set, when the measurements from at least one sensor are deemed unreliable, said secondary flight characteristic being independent of any measurement by the or each sensor deemed unreliable done when the measurements from that sensor are deemed unreliable.

Abstract translation: 提供了一种用于显示飞行器飞行特性的装置。 该装置包括用于选择性地显示飞行器的飞行特性的显示器，作为分配给来自静压力，总压力和入射传感器的测量值的可信度状态的函数，被配置为选择性地显示主要的飞行特征集，其包括至少 当来自所述传感器的测量被认为是可靠的时，来自所述传感器之一的测量的一个飞行特征，以及与所述主组不同的第二组飞行特征，包括至少一个辅助飞行特征，其被设计成替换对方飞行 当来自至少一个传感器的测量值被认为不可靠时，当从该传感器的测量被认为不可靠时，所述次要飞行特性与所述传感器或每个传感器的任何测量无关，当所述传感器的测量被认为是不可靠的。

公开(公告)号：US20140327699A1

公开(公告)日：2014-11-06

申请号：US14269504

申请日：2014-05-05

Applicant: DASSAULT AVIATION

Inventor： Sebastien DUPONT DE DINECHIN ,  Fabrice Vallete

IPC: B64D45/00 ,  G06T13/00 ,  G06T19/00

CPC classification number: B64D45/00 ,  G01C23/00 ,  G06F3/147 ,  G06T13/00 ,  G06T19/006 ,  G09G5/14 ,  G09G2340/12 ,  G09G2340/125 ,  G09G2354/00 ,  G09G2358/00 ,  G09G2380/12

Abstract: A device is provided for assisting in the piloting of a vehicle, in particular an aircraft. The device includes a surface displaying images and a display management unit for images designed to be displayed on the display surface superimposed on a view of the outside landscape. The management unit is capable of commanding the display of piloting information images on the display surface. The management unit is capable of commanding the display, for at least one of the piloting information images, of an animation intended to attract a user's attention to that piloting information image, the animation comprising the display of an alert image and the shrinkage of the alert image.

Abstract translation: 提供了一种用于辅助驾驶车辆，特别是飞机的装置。 该装置包括显示图像的表面和用于被设计为显示在叠加在外部景观的显示表面上的图像的显示管理单元。 管理单元能够命令在显示面上显示引导信息图像。 管理单元能够命令用于至少一个驾驶信息图像的旨在吸引用户注意该导航信息图像的动画，该动画包括警报图像的显示和警报的收缩 图片。

公开(公告)号：US20140207367A1

公开(公告)日：2014-07-24

申请号：US14154063

申请日：2014-01-13

Applicant: DASSAULT AVIATION

Inventor： Jean-Michel PFLIMLIN ,  Gildas DAUPHIN

IPC: G01C21/00

CPC classification number: G01C21/00 ,  G01C21/005 ,  G05D1/0055 ,  G05D1/101 ,  G08G5/0039

Abstract: A Method for defining a fall back route comprising of way points, for a mobile machine, in a 3D zone (ZNd) of displacement having convex zones (Zni, i=1 to 7) each describing a polygon in any plane perpendicular to a Z axis over a considered region (Hj, j=1 to 6) of a Z axis, according to which: set of beacons points (PBk, k=1 to 7) is defined, such that the edges of the Voronoi diagram associated with the said set of beacon points separate therebetween the polygons described by the convex zones in a plane perpendicular to the Z axis over the said region.

Abstract translation: 一种用于定义回落路线的方法，其包括用于移动机器的具有凸区域（Zni，i = 1至7）的位移的3D区域（ZNd）中的路点，每个区域描述在垂直于Z的任何平面中的多边形 轴定位在Z轴的考虑区域（Hj，j = 1至6）上，根据该坐标轴定义信标点集合（PBk，k = 1至7），使得与...相关联的Voronoi图的边缘 所述一组信标点在两者之间分开，所述多边形在与所述区域上的Z轴垂直的平面中由凸区描述。

公开(公告)号：US20130187448A1

公开(公告)日：2013-07-25

申请号：US13748703

申请日：2013-01-24

Applicant: DASSAULT AVIATION

Inventor： Renaud LOISON ,  Olivier SAVIN

IPC: B64D25/00

CPC classification number: B64D25/00 ,  B64D41/00 ,  B64D2041/005 ,  H02J4/00 ,  H02J9/06 ,  H02J2001/004 ,  Y02B90/14 ,  Y02T90/36

Abstract: This assembly (24) includes an emergency electricity generator (60). The electricity generator assembly (24) is controllable between an inactive rest configuration and an active configuration for producing energy in which the emergency electricity generator (60) delivers emergency electric energy to the electric network (20), without being electrically powered by the electric network (20). The emergency electric power generation assembly (24) is able to be placed in an intermediate standby configuration, in which the emergency electric power generation assembly (24) is electrically powered by the electric network (20) so that the emergency electricity generator (60) produces standby electric energy of lower power than the power delivered by the emergency electricity generator (60) in the active configuration.

Abstract translation: 该组件（24）包括紧急发电机（60）。 发电机组件24在非活动休止配置和活动配置之间是可控制的，用于产生能量，其中紧急发电机（60）向电网（20）提供紧急电能，而不用电网 （20）。 紧急发电组件24能够被放置在中间待机配置中，其中紧急发电组件24由电网20供电，使得紧急发电机60被应用在发电组件24上。 产生比由应急发电机（60）在主动配置中输送的功率低的待机电能。

公开(公告)号：US20250162720A1

公开(公告)日：2025-05-22

申请号：US18950279

申请日：2024-11-18

Applicant: DASSAULT AVIATION

Inventor： Alexandre AUROY ,  Thomas BARRACO ,  Zoé SIGRIST

IPC: B64D27/35

Abstract: An aircraft power supply network and associated aircraft, the power supply network includes a first engine and a second engine, a first and a second set of loads, an auxiliary electrical source and a first electrical machine connected to the first engine. The power supply network also includes a first converter connected to the first electrical machine, a first interconnection bus connected to the first converter by a first primary switch and to the first set of loads and a second electrical machine connected to the second motor. The power supply network further includes a second converter, a second interconnection bus, connected to the second converter by a second primary switch and to the second set of loads, a sharing bus connected to the first interconnection bus by a first inter-bus switch, connected to the second interconnection bus by a second inter-bus switch and connected to the auxiliary electrical source.

公开(公告)号：USD1071829S1

公开(公告)日：2025-04-22

申请号：US29891357

申请日：2023-05-04

Applicant: DASSAULT AVIATION

Designer： Quentin Foos ,  Maxime Nicot ,  Mathieu Hautem

公开(公告)号：US12227288B2

公开(公告)日：2025-02-18

申请号：US17872676

申请日：2022-07-25

Applicant: DASSAULT AVIATION

Inventor： Angélique Beaucamp ,  Nicolas Le Corre ,  François Pineau

IPC: B64C25/42 ,  B64C25/32 ,  B64C25/48

Abstract: A device is for assisting the taxiing of an aircraft, using at least one engine and at least one braking member. The device includes a control member, adapted to be actuated by a pilot from a neutral position to define a taxiing piloting command 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 central controller is also configured to pilot at least one braking member of the aircraft to apply the taxiing piloting command defined by the pilot.