公开(公告)号：US10761326B2

公开(公告)日：2020-09-01

申请号：US16213921

申请日：2018-12-07

Applicant: THALES

Inventor： Bruno Aymeric ,  Siegfried Rouzes

IPC: G02B27/01 ,  G06F3/01 ,  G02B27/00 ,  G01C23/00 ,  G05D1/00 ,  G06K9/00

Abstract: A dual harmonization method for a head-worn display system for making the display of piloting information of an aircraft conform with the outside real world includes a step of acquisition of N measurements {circumflex over (K)}l of head postures by a series of different sightings Vi, each of which aligns a sighting pattern, situated at a different fixed position Pi on the display D0 with a sighting vector that is a function of the position Pi, then a step of computation of the matrix of relative orientation M01 between the display D0 in a tilted position of engagement in the field of view and the tracking first element D1 as the right matrix {circumflex over (D)} that is the solution of the dual harmonization system of equations Ĝ·{circumflex over (K)}i·{circumflex over (D)}·{right arrow over (x)}i={right arrow over (y)}0 for i varying from 1 to N, the vector {right arrow over (y0)} denoting the vector in the inertial reference frame of the platform corresponding to the target point targeted in the outside real world and being unknown; and the left matrix Ĝ being the matrix M23 of relative orientation between the fixed second element D2 and the attitude inertial device D3, which is potentially incorrect but assumed constant as a function of time, and which, when it is unknown, requires at least four measurements {circumflex over (K)}l. A head-up display system is configured to implement the dual harmonization method.

公开(公告)号：US20180173387A1

公开(公告)日：2018-06-21

申请号：US15832619

申请日：2017-12-05

Applicant: THALES

Inventor： Frédéric Scarfone ,  Patrice Malot ,  Bruno Aymeric ,  Jonathan Barreau

IPC: G06F3/0484 ,  B64D43/00 ,  G06F3/0481

Abstract: Methods for graphically managing a pitch scale displayed in an on-board viewing system for an aircraft, the viewing system comprises a graphics computer carrying out the graphical management of the symbols and a viewing screen. The symbolic representation displayed on the viewing screen includes an angular pitch scale, a symbol, referred to as the aircraft icon, that is representative of the attitude of the aircraft and a symbol, referred to as the speed vector that is representative of the direction of the speed of the aircraft. The angular distance separating the “bars” of the scale varies so that the symbols representative of the attitude of the aircraft and of the speed vector remain constantly close to one of the two bars of the scale, even in the event of a strong crosswind. The shape of the bars is either constant or variable.

公开(公告)号：US10332404B2

公开(公告)日：2019-06-25

申请号：US15357702

申请日：2016-11-21

Applicant: THALES

Inventor： Bruno Aymeric ,  Xavier Servantie ,  Matthieu Claybrough

IPC: G01C23/00 ,  G05D1/00 ,  G05D3/00 ,  G06F7/00 ,  G06F17/00 ,  G08G5/00 ,  B64D43/00

Abstract: A method for the three-dimensional representation of the trajectory of an aircraft in flight implemented in a navigation system of an aircraft is provided. The flight plan of the aircraft comprises imposed georeferenced trajectories and predicted non-georeferenced trajectories. When the trajectory of the aircraft is dependent on a non-georeferenced flight setpoint, the three-dimensional representation method is an iterative process comprising the following steps: computing a predicted trajectory arising from at least one computed trajectory extending over a determined distance or duration; computing a smoothed trajectory from the predicted trajectory in order to obtain a resulting trajectory; computing a displayed trajectory, the trajectory being equal to the resulting trajectory corrected for constant deviations or deviations depending on the application of setpoints from the flight director; and displaying the displayed trajectory.

公开(公告)号：US10018482B2

公开(公告)日：2018-07-10

申请号：US15357735

申请日：2016-11-21

Applicant: THALES

Inventor： Bruno Aymeric ,  Xavier Servantie ,  Matthieu Claybrough

IPC: G01C23/00 ,  G08G5/00

CPC classification number: G01C23/00 ,  G01C23/005 ,  G08G5/0021 ,  G08G5/0086

Abstract: A method for the three-dimensional synthetic representation of the trajectory of an aircraft in flight being implemented in a flight and navigation system of an aircraft comprising a display system allowing synthetic images to be displayed, the flight plan of the aircraft comprises a predicted trajectory dependent on a non-georeferenced flight setpoint, the display of the predicted trajectory taking the form of a path represented by two limits separated by a determined width. The path comprises two branches, each branch positioned on the side of one of the two limits, each branch represented by a straight segment whose origin is a point located on the path at the current time and whose terminus is a point located at a determined distance away from the point of origin, the slope of the straight segment representative of the tangent to the predicted trajectory at the current time.

公开(公告)号：US20150364045A1

公开(公告)日：2015-12-17

申请号：US14737362

申请日：2015-06-11

Applicant: THALES

Inventor： Sylvain LISSAJOUX ,  Bruno Aymeric ,  Thibaut Debard

IPC: G08G5/00

CPC classification number: G08G5/0047 ,  G01C23/00 ,  G05D1/0202 ,  G05D1/0607 ,  G08G5/0021

Abstract: A method and device for determining a control set point of an aircraft, an associated computer program and an aircraft are disclosed. In one aspect, the method includes calculating a performance scale in the form of slope values of the aircraft, the performance scale including a slope characteristic value, the slope characteristic value being associated with a corresponding performance characteristic value. The method also includes acquiring a guidance set point and displaying the acquired guidance set point, in the form of a slope value with respect to the performance scale. The method further includes determining a slope characteristic value associated with a guidance set point displayed in the form of a slope value, and calculating an aircraft control set point, the control set point being calculated relative to the performance characteristic value corresponding to the determined slope characteristic value.

Abstract translation: 公开了一种用于确定飞行器，相关联的计算机程序和飞机的控制设定点的方法和装置。 一方面，该方法包括以飞机的斜率值的形式计算性能量表，该性能量表包括斜率特征值，斜率特征值与相应的性能特征值相关联。 该方法还包括以相对于性能量表的斜率值的形式获取引导设定点并显示所获取的引导设定点。 该方法还包括确定与以斜率值形式显示的引导设定点相关联的斜率特征值，以及计算飞行器控制设定点，控制设定点是相对于与所确定的斜率特性对应的性能特征值计算的 值。

公开(公告)号：US20140074323A1

公开(公告)日：2014-03-13

申请号：US14020731

申请日：2013-09-06

Applicant: Thales

Inventor： Cecile ANDRE ,  Francois Michel ,  Yannick Le Roux ,  Bruno Aymeric

IPC: G06F3/0481

CPC classification number: G06F3/04815 ,  G08G5/0021 ,  G08G5/0039

Abstract: The general area of the invention is that of methods for managing flight plans by an avionic system comprising a visualization device and a touch-sensitive interface. The visualization device displays a cartographic representation of the terrain flown over, aeronautical data and a flight plan composed of a set of segments connecting together certain aeronautical waypoints. The management method contains several steps, a first editing step activated by touch-sensitive designating of any point of the flight plan, a second modification of the flight plan step activated by a touch-sensitive movement, the end of the touch-sensitive movement triggering a movement or an addition or the removal of a waypoint. The method also makes it possible to easily manage the airways in order to incorporate them into a flight plan during modification.

Abstract translation: 本发明的一般领域是由包括可视化装置和触敏界面的航空电子系统管理飞行计划的方法。 可视化设备显示地形飞越的图形表示，航空数据和由连接某些航空航路点的一组段组成的飞行计划。 管理方法包含几个步骤，通过触摸敏感指定飞行计划任一点激活的第一编辑步骤，触敏运动激活的飞行计划步骤的第二修改，触敏运动触发的结束 航路的移动或添加或移除。 该方法还可以容易地管理航空公司，以便在修改期间将其并入飞行计划。

公开(公告)号：US20180075632A1

公开(公告)日：2018-03-15

申请号：US15652801

申请日：2017-07-18

Applicant: THALES

Inventor： Luc Baron ,  Christophe Garnavault ,  Bruno Aymeric ,  Yannick Le Roux

IPC: G06T11/60 ,  G09G5/14 ,  G09G5/00 ,  B64D43/00

CPC classification number: G06T11/60 ,  B64D43/00 ,  G01C23/00 ,  G06F3/14 ,  G06F3/147 ,  G08G5/0021 ,  G09G5/005 ,  G09G5/14 ,  G09G2340/0442 ,  G09G2340/12 ,  G09G2354/00 ,  G09G2380/12

Abstract: The present invention relates to a system (14) for displaying avionic data on at least one display space of an aircraft cockpit, comprising a processing module (23) configured to receive a message to be displayed indicating an event and to associate the content of this message with one of the display formats, a display module (25) configured to display the received message superimposed on at least one current display format, displayed in a respective display space and an acquisition module (27) configured to acquire a display control command relative to the received message. The display module (25) is further configured to display the display format associated with said message on at least one display space in case of acquisition of the display control command relative to said message.

公开(公告)号：US09422051B2

公开(公告)日：2016-08-23

申请号：US14015904

申请日：2013-08-30

Applicant: Thales

Inventor： Bruno Aymeric ,  Yannick Le Roux ,  Sylvain Hourlier

IPC: G06F3/0481 ,  B64C19/00 ,  G05D1/08 ,  G01C23/00 ,  G02B27/01

CPC classification number: B64C19/00 ,  G01C23/005 ,  G02B27/017 ,  G02B2027/0141 ,  G02B2027/0187 ,  G05D1/0858

Abstract: Hover hold aid systems for helicopters are described. One system comprises a navigation system that determines a helicopter's current position in relation to a terrestrial frame of reference and a helmet-mounted visualization system comprising a helmet-mounted display (HMD) and at least one symbol generation processing device that generates symbols in the HMD at fixed positions in relation to the terrestrial frame of reference. The symbols are displayed in an angular field of display of the HMD. When the helicopter has to home or stay in a vicinity of a predetermined position, the at least one symbol generation processing device calculates a first and a second representation containing a first target and a second target referenced in the terrestrial frame of reference. The first target is located in the direction of the homing course to the predetermined position. The second target is located in a direction perpendicular to this same course.

Abstract translation: 描述了用于直升机的悬停支援系统。 一个系统包括导航系统，其确定相对于地面参考系的直升机的当前位置;以及头盔安装的可视化系统，其包括头盔安装显示器（HMD）和至少一个在HMD中产生符号的符号生成处理设备 在与地面参照系相关的固定位置。 符号显示在HMD的显示的角度场中。 当直升机必须回家或停留在预定位置附近时，至少一个符号产生处理装置计算包含在地面参考系中参考的第一目标和第二目标的第一和第二表示。 第一目标位于预定位置的归位进程的方向。 第二个目标位于垂直于同一路线的方向。

公开(公告)号：US20140156114A1

公开(公告)日：2014-06-05

申请号：US14069272

申请日：2013-10-31

Applicant: THALES

Inventor： Bruno Aymeric ,  Cécile Andre ,  Yannick Le Roux ,  François Michel

IPC: G08G5/00

CPC classification number: G08G5/003 ,  G01C23/00 ,  G08G5/0021 ,  G08G5/0034 ,  G08G5/0039

Abstract: The general field of the invention is that of methods of graphic representation, modification and validation of an aeronautical flight plan for an aircraft avionics system. The system comprises means for computing and generating said flight plan, a task management system, a visualization device displaying a graphic representation of said flight plan and a man-machine interface suitable for making selections, modifications or additions to the information contained in said graphic representation, said selections, modifications and additions being taken into account by the task management system, said graphic representation containing a timeline on which feature at least the various phases of the flight plan and the information corresponding to said phases. The method according to the invention contains a step of displaying at least one item of information depending on several parameters and the graphic representation of which depends on the level of available information about said parameters.

Abstract translation: 本发明的一般领域是用于飞机航空电子系统的航空飞行计划的图形表示，修改和验证的方法。 该系统包括用于计算和产生所述飞行计划的装置，任务管理系统，显示所述飞行计划的图形表示的可视化装置以及适于对包含在所述图形表示中的信息进行选择，修改或添加的人机界面 ，所述选择，修改和添加被所述任务管理系统考虑在内，所述图形表示包含至少在飞行计划的各个阶段的特征以及对应于所述阶段的信息的时间线。 根据本发明的方法包括根据几个参数显示至少一个信息项的步骤，并且其图形表示取决于关于所述参数的可用信息的级别。

公开(公告)号：US12013543B2

公开(公告)日：2024-06-18

申请号：US17422787

申请日：2019-12-18

Applicant: THALES

Inventor： Joël Baudou ,  Mathieu Balet ,  Bruno Aymeric

IPC: G02B27/01 ,  A42B3/04

CPC classification number: G02B27/0176 ,  A42B3/042 ,  A42B3/0453 ,  G02B2027/0156 ,  G02B2027/0159 ,  G02B2027/0178 ,  G02B2027/0181

Abstract: A helmet-mounted display systems includes a front mechanical arch comprising a display device and a means for holding and adjusting the display device in the vertical plane, the means consisting of a first vertical support surface comprising an oblong port and a screw/spring assembly, the screw passing through the oblong port and being fastened in a mechanical structure of the display device, the display device being capable of rotating in such a way as to make it retractable. The display system comprises a means for roll adjustment and repositioning of the display device, the adjustment means consisting of a second vertical support surface, normal to the first support surface, and a knurl screw attached to the mechanical structure of the display device, the end of the screw resting on the second support surface when the display device is in the use position.