Thales

Bruno Aymeric

Yannick Le Roux

Xavier Servantie

Sylvain Lissajoux

Matthieu Claybrough

Siegfried Rouzes

Joël Baudou

Thierry Ganille

Denis Bonnet

Sylvain Hourlier

Cécile Andre

Guy Deker

Michel Roger

François Michel

Nicolas Berthou

Johanna Lux

Pierre-Yves Dumas

Didier Poisson

Christophe Garnavault

Mathieu Balet

Thibaut Debard

Marc Lefort

Frédéric Scarfone

Sébastien Ellero

Patrice Malot

Jonathan Barreau

Bruno Capelle

Luc Baron

Yannick Leroux

Romain Sacheau

Joel Viala

Patrice Eudeline

Jean-Yves Favard

Pierre-Olivier Garros

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.

Helmet display system comprising a removable helmet-mounted display compatible with the use of binoculars

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.

Helmet-mounted display system comprising a device for aligning and retracting the display device

The invention relates to the management of binocular rivalry, and by extension of attentional rivalry, in a display system. A method of the invention may include 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.

Binocular rivalry management

The invention relates to a display system included in a device for traveling a path between at least two distinct points and for using at least one heading datum, wherein the display system comprises at least:

Display system, related display method and computer program

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)}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 Dwith a sighting vector that is a function of the position Pi, then a step of computation of the matrix of relative orientation Mbetween the display Din a tilted position of engagement in the field of view and the tracking first element Das the right matrix {circumflex over (D)} that is the solution of the dual harmonization system of equations &#x11c;&#xb7;{circumflex over (K)}&#xb7;{circumflex over (D)}&#xb7;{right arrow over (x)}={right arrow over (y)}for i varying from 1 to N, the vector {right arrow over (y)} 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 &#x11c; being the matrix Mof relative orientation between the fixed second element Dand the attitude inertial device D, 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)}. A head-up display system is configured to implement the dual harmonization method.

Dual harmonization method and system for a head-worn display system for making the display of piloting information of an aircraft conform with the outside real world

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.

Method for graphically managing a pitch scale in an on-board viewing system for an aircraft

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)}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 D, then a step of joint computation of the matrices of relative orientation Mand Mas joint solutions of the dual harmonization &#xdb;=&#x11c;&#xb7;{circumflex over (K)}&#xb7;{circumflex over (D)}, i varying from 1 to N, in which &#xdb;is the transpose of the matrix M(image(i)/0) of relative orientation of the image(i) of rank i relative to the display D, with Mand Mrespectively equal to the right and left matrices {circumflex over (D)} and &#x11c;. A worn head-up display system is configured to implement the dual harmonization method.

Dual harmonization method and system for a worn head-up display system with a removable attitude inertial device in the cockpit

The present invention relates to a system () for displaying avionic data on at least one display space of an aircraft cockpit, comprising a processing module () 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 () configured to display the received message superimposed on at least one current display format, displayed in a respective display space and an acquisition module () configured to acquire a display control command relative to the received message. The display module () 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.

System for displaying avionic data on at least one display space, aircraft cockpit including such a system, related display method and computer program product

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.

Method for computing the representation of the trajectory of an aircraft in flight

A method of synthetic representation of elements of interest in a viewing system for aircraft, the viewing system comprises location sensors, a cartographic database and a database of elements of interest, an image sensor, a unit for processing images and a unit for generating three-dimensional digital images representative of the terrain overflown and a viewing device, wherein, when the terrain overflown comprises an element of interest, the method of synthetic representation comprises: a first step of searching for and detecting the element of interest in each image of a sequence of images, and; a second step of generating three-dimensional digital images representative of the terrain overflown, the element of interest represented according to a first representation if it has not been detected in any of the images of the sequence of images and according to a second representation if it is detected.

Method of synthetic representation of elements of interest in a viewing system for aircraft

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.

Method and device for displaying vertical constraints of an aircraft, associated computer program product and aircraft

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.

Electronic device and method for aiding the piloting of an aircraft, with calculation and display of at least a roll margin, related computer program product

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.

Method for computing and representing deviations from the trajectory of an aircraft in flight

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.

Flight management method and system

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 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.

Growing community of inventors

St. Medard en Jalles, France

Bruno Aymeric