公开(公告)号：US20190108813A1

公开(公告)日：2019-04-11

申请号：US16150231

申请日：2018-10-02

Applicant: THALES

Inventor： Sylvain HOURLIER ,  Bruno AYMERIC

IPC: G09G5/00 ,  G09G5/10 ,  G09G5/37 ,  G02B27/01

Abstract: The management of binocular rivalry, and by extension of attentional rivalry, in a display system is provided. The method includes the steps of determining visual surroundings parameters; determining a risk of visual suppression by binocular rivalry between an element of the visual surroundings and an element displayed by the display device on the basis of the visual surroundings parameters; and, on the basis of the determined risk, adjusting the display. Developments of the invention describe the management of the luminance, of the chrominance and of the geometry of the displayed elements. Optimizations in the field of avionics are described. Software and system aspects are described (e.g. brightness sensors and/or gaze-tracking sensors, monocular system).

公开(公告)号：US20190196198A1

公开(公告)日：2019-06-27

申请号：US16219608

申请日：2018-12-13

Applicant: THALES

Inventor： Bruno AYMERIC ,  Siegfried ROUZES ,  Bruno CAPELLE ,  Sébastien ELLERO

IPC: G02B27/01 ,  G06K9/00 ,  G06F3/01 ,  G05D1/10

Abstract: A dual harmonization method for a worn head-up display system for making the display of piloting information of an aircraft on a display conform with the outside real world includes a step of acquisition of N measurements {circumflex over (K)}ι of head posture detection by a series of sightings Vi corresponding to images oriented according to orientations Oi of one and the same photograph taken by a camera, secured to and aligned with the attitude inertial device D3, then a step of joint computation of the matrices of relative orientation M01 and M23 as joint solutions of the dual harmonization ÛiĜ·{circumflex over (K)}i·{circumflex over (D)}, i varying from 1 to N, in which Ûι is the transpose of the matrix M(image(i)/0) of relative orientation of the image(i) of rank i relative to the display D0, with M01 and M23 respectively equal to the right and left matrices {circumflex over (D)} and Ĝ. A worn head-up display system is configured to implement the dual harmonization method.

公开(公告)号：US20140097291A1

公开(公告)日：2014-04-10

申请号：US14015904

申请日：2013-08-30

Applicant: Thales

Inventor： Bruno AYMERIC ,  Yannick Le Roux ,  Sylvain Hourlier

IPC: B64C19/00

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

Abstract: The general area of the invention is that of hover hold aid systems for helicopters. The system comprises navigation means; a helmet-mounted visualization system containing a helmet-mounted display incorporated in the pilot's helmet and means for generating symbols in said helmet-mounted display at fixed positions in relation to a terrestrial frame of reference, said symbols being displayed in the angular field of display of the helmet-mounted display. When the helicopter has to home or stay in the vicinity of a predetermined position, the symbol generation means calculate a first and a second representation containing a first target and a second target referenced in said terrestrial frame of reference, the first target located in the direction of the homing course to the predetermined position, the second target located in a direction perpendicular to this same course.

Abstract translation: 本发明的一般领域是用于直升机的悬停支援系统。 该系统包括导航装置; 一种头盔安装的可视化系统，其包含结合在驾驶员头盔中的头戴式显示器的显示器，以及用于在所述头盔安装显示器中相对于地面参考系固定位置产生符号的装置，所述符号以显示的角度场显示 的头戴式显示器。 当直升机必须回家或停留在预定位置附近时，符号产生装置计算包含在所述地面参照系中参考的第一目标和第二目标的第一和第二表示，所述第一目标位于方向 所述第二目标位于与所述相同路线垂直的方向上。

公开(公告)号：US20170168560A1

公开(公告)日：2017-06-15

申请号：US15375061

申请日：2016-12-09

Applicant: THALES

Inventor： Romain SACHEAU ,  Bruno AYMERIC ,  Jonathan BARREAU

IPC: G06F3/01 ,  B64D43/00 ,  G06F1/16

CPC classification number: G06F3/012 ,  B64D43/00 ,  G01C23/005 ,  G02B27/017 ,  G02B27/0179 ,  G06F1/163

Abstract: The general field of the invention is that of methods of displaying an “attitude director indicator” in a head viewing system for aircraft comprising: a head support bearing a viewing device; a detection of posture; sensors for detecting the various parameters defining the attitude of the said aircraft; means for computing and graphically generating the said attitude, the set of parameters displayed being termed the “attitude director indicator”; In the method according to the invention, when the head support is oriented in a determined direction making, with the horizon line and/or with the “speed vector”, an angle greater than a first value, and/or when at least one of the attitude parameters of the aircraft becomes greater than a second value, the attitude director indicator is displayed locally in a reference frame tied to the head support and in the field of the viewing device.

公开(公告)号：US20150084794A1

公开(公告)日：2015-03-26

申请号：US14492864

申请日：2014-09-22

Applicant: THALES

Inventor： Bruno AYMERIC ,  Xavier SERVANTIE ,  Cécile ANDRE

IPC: G08G5/00

CPC classification number: G08G5/0047 ,  G01C5/005 ,  G01C23/00 ,  G01D7/04

Abstract: A navigation aid information display device of an aircraft and primary flight display for an aircraft are disclosed. In one aspect, the navigation aid information display system includes a display screen including at least one first display area configured to display a first altitude scale including graduations, the current altitude of the aircraft on the first scale, and a set altitude value. The graduations of the first scale are distributed on an arc of a first disc including a first needle centered in the disc and the first needle is configured to indicate the current altitude on the first scale. The distribution of the graduations on the arc is nonlinear and symmetrical relative to a graduation corresponding to the set altitude value and defines extension graduations decreasing from the set altitude value.

Abstract translation: 公开了飞机的导航辅助信息显示装置和飞行器的主飞行显示器。 一方面，导航辅助信息显示系统包括显示屏幕，其包括被配置为显示包括刻度的第一高度刻度，第一刻度上的飞行器的当前高度以及设定的高度值的至少一个第一显示区域。 第一刻度的刻度分布在包括在盘中心的第一针的第一盘的圆弧上，并且第一针被配置为指示第一刻度上的当前高度。 圆弧上的刻度分布相对于与设定的高度值相对应的刻度是非线性的和对称的，并且定义从设定的高度值减小的延伸刻度。

公开(公告)号：US20220128823A1

公开(公告)日：2022-04-28

申请号：US17423917

申请日：2019-12-18

Applicant: THALES

Inventor： Joël BAUDOU ,  Bruno AYMERIC

IPC: G02B27/01 ,  G02B27/00

Abstract: A modular helmet display system includes at least one helmet shell, binoculars and a display device. The helmet shell includes a mechanical arch fixedly mounted on the front part of the helmet, and the mechanical arch includes at least one first device for attaching the binoculars. In the system, the mechanical arch includes a second device for attaching the display device. The display device may include a posture detection device and an adjustment mechanism. The display system may include a mechanical cover which is mounted in place of the display device, the shape of the cover being adapted so as to hide the upper part of the helmet. A mobile visor can be mounted on the mechanical arch.

公开(公告)号：US20170154534A1

公开(公告)日：2017-06-01

申请号：US15357702

申请日：2016-11-21

Applicant: THALES

Inventor： Bruno AYMERIC ,  Xavier SERVANTIE ,  Matthieu CLAYBROUGH

IPC: G08G5/00 ,  B64D43/00

CPC classification number: G08G5/0021 ,  B64D43/00 ,  G01C23/005 ,  G08G5/0052

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：US20170004713A1

公开(公告)日：2017-01-05

申请号：US15201258

申请日：2016-07-01

Applicant: THALES

Inventor： Matthieu CLAYBROUGH ,  Bruno AYMERIC ,  Sylvain LISSAJOUX

IPC: G08G5/00 ,  G02B27/01

CPC classification number: G08G5/0065 ,  G01C21/20 ,  G01C23/00 ,  G02B27/0101 ,  G02B2027/0141 ,  G02B2027/0183

Abstract: A method and device for displaying vertical constraints of an aircraft, an associated program produce and aircraft are disclosed. In one aspect, the vertical constrains are displayed on a display device of the aircraft, the display device being part of an aircraft piloting system, the method being implemented by an electronic device that is part of the aircraft piloting system. The method includes acquiring at least one vertical constraint of the aircraft, computing a representative slope value associated with the vertical constraint, and displaying a symbol depicting the vertical constraint at the representative slope value associated with the vertical constraint on a slope scale

Abstract translation: 公开了一种用于显示飞行器，相关程序产品和飞行器的垂直约束的方法和装置。 在一个方面，垂直约束显示在飞行器的显示装置上，显示装置是飞行器驾驶系统的一部分，该方法由作为飞机驾驶系统一部分的电子装置实现。 该方法包括获取飞行器的至少一个垂直约束，计算与垂直约束相关联的代表性斜率值，并且以与斜率尺度上的垂直约束相关联的代表性斜率值显示描绘垂直约束的符号

公开(公告)号：US20160363459A1

公开(公告)日：2016-12-15

申请号：US15176682

申请日：2016-06-08

Applicant: THALES

Inventor： Sylvain LISSAJOUX ,  Bruno AYMERIC ,  Didier POISSON

IPC: G01C23/00 ,  B64D43/02

CPC classification number: G01C23/005 ,  B64D43/02

Abstract: This electronic device for aiding with the piloting of an aircraft includes: an acquisition module, configured to acquire a current value of the roll angle of the aircraft; a computing module configured to compute a roll angle limit corresponding to a beginning of stalling of the aircraft; and a display module, configured to display, on a screen, a first symbol indicating a current orientation of the aircraft. The computing module is configured to compute at least one roll margin, each roll margin depending on a corresponding roll angle limit and the current value of the roll angle, and the display module is configured, when the display condition is verified, to display, on the screen, at least one second symbol positioned relative to the first symbol, the deviation between each second symbol and the first symbol representing a respective roll margin.

Abstract translation: 用于辅助飞机驾驶的该电子设备包括：获取模块，被配置为获取飞行器的滚动角度的当前值; 计算模块，被配置为计算对应于飞行器停止开始的滚转角度限制; 以及显示模块，被配置为在屏幕上显示指示飞行器的当前方向的第一符号。 计算模块被配置为计算至少一个滚动边缘，每个滚动边距取决于相应的滚动角度限制和滚动角度的当前值，并且当显示条件被验证时，显示模块被配置为显示在 所述屏幕，相对于所述第一符号定位的至少一个第二符号，每个第二符号与所述第一符号之间的偏差表示相应的卷边距。

公开(公告)号：US20150262490A1

公开(公告)日：2015-09-17

申请号：US14627645

申请日：2015-02-20

Applicant: THALES

Inventor： Guy DEKER ,  Michel ROGER ,  Bruno AYMERIC

IPC: G08G5/00

CPC classification number: G08G5/0039 ,  G05D1/101 ,  G08G5/0013 ,  G08G5/0021 ,  G08G5/0047 ,  G08G5/0052 ,  G08G5/0095

Abstract: A method and system, for flight management of an aircraft flying on a trajectory shifted with respect to a flight plan comprising a plurality of constrained waypoints, comprises a step of determining and displaying at least one point of the trajectory, termed decision point, beyond which the aircraft can no longer rejoin a constrained waypoint of the flight plan by determining a point of intersection between the trajectory and a rejoining trajectory steering towards the selected constrained waypoint, the rejoining trajectory complying with at least one predefined criterion.

Abstract translation: 一种用于对在相对于包括多个受限航路点的飞行计划移动的轨迹上飞行的飞行器的飞行管理的方法和系统包括确定和显示所述轨迹的至少一个点（被称为决策点）的步骤，超过该点 飞行器不能再通过确定轨迹与朝向选定的受限航路点转向的重合轨迹之间的交点，重新加入飞行计划的约束航点，该重合轨迹符合至少一个预定准则。