Abstract: The present invention relates to a display device for a glass cockpit of an aircraft, intended to provide video streams to a plurality of viewing screens of said glass cockpit, said aircraft being partitioned into a secured area, a so-called avionic world (AW), and a non-secured area, a so-called open world (OW), said system comprising at least one first port intended to receive first data to be displayed from a system (210, 310, 410) belonging to the avionic area and at least one second port intended to receive second data to be displayed from a system (220, 320, 420) belonging to the open world, the display device comprising: predetermined hardware resources allocated to the processing of the second data; a processor (241, 341, 441), belonging to the avionic area, adapted to controlling the hardware resources used by said processing and interrupting this processing if said hardware resources used exceed said allocated resources.

Abstract: Disclosed is a method and system for avoiding collision between an aircraft A and an intruder aircraft. The method and system involve determining avoidance presets to avoid a collision between the aircraft A and the intruder aircraft, in which the avoidance presets comprise a vertical speed preset. The presets are determined from avoidance information received from an anticollision system, and the determined avoidance presets are transmitted to at least one guidance device that guides the aircraft A based on the avoidance presets.

Abstract: The inventive flight control assisting device comprises first means (4) for determining the actual aircraft flight conditions, second means (5) for determining, with the aid of said actual flight conditions and a predetermined pattern, a minimum approaching distance corresponding to a minimum distance between projections on the horizontal plane of the aircraft actual position and a touch-down point when said aircraft moves downwards and decelerates according to an optimised approach in such a way that stabilised approaching conditions are attained, and display means (7) for displaying at least said minimum approaching distance on a navigation screen (9) in the form of a first circular arc focused on a position relative to the aircraft which displays the touch-down position.

Abstract: The present invention relates to a display device for a glass cockpit of an aircraft, intended to provide video streams to a plurality of viewing screens of said glass cockpit, said aircraft being partitioned into a secured area, a so-called avionic world (AW), and a non-secured area, a so-called open world (OW), said system comprising at least one first port intended to receive first data to be displayed from a system (210, 310, 410) belonging to the avionic area and at least one second port intended to receive second data to be displayed from a system (220, 320, 420) belonging to the open world, the display device comprising: predetermined hardware resources allocated to the processing of the second data; a processor (241, 341, 441), belonging to the avionic area, adapted to controlling the hardware resources used by said processing and interrupting this processing if said hardware resources used exceed said allocated resources.

Abstract: A method and device for assisting the lateral control of an aircraft running on a runway employ a detector for measuring a lateral deviation of the aircraft relative to a lateral alignment beam transmitted by a radio transmitter installed on the ground, the lateral deviation representing an angular deviation between a straight line passing through the radio transmitter and the detector and the centerline of the runway. A calculator calculates a first distance, defined along the runway, between the position of the pilot in the cockpit and the radio transmitter. A central unit determines, from the lateral deviation and the first distance, a line intended to correspond with the centerline of the runway. A head up display device displays the line on a display screen, superimposed on the environment existing in front of the aircraft and the centerline of the runway.

Abstract: The inventive flight control assisting device comprises first means (4) for determining the actual aircraft flight conditions, second means (5) for determining, with the aid of said actual flight conditions and a predetermined pattern, a minimum approaching distance corresponding to a minimum distance between projections on the horizontal plane of the aircraft actual position and a touch-down point when said aircraft moves downwards and decelerates according to an optimised approach in such a way that stabilised approaching conditions are attained, and display means (7) for displaying at least said minimum approaching distance on a navigation screen (9) in the form of a first circular arc focused on a position relative to the aircraft which displays the touch-down position.

Abstract: A method for landing an aircraft includes determining the aircraft's deviation from its approach path so as to define a first point of the aircraft's heading. A first straight line passing through the first point and through a second point defining the ground orientation of the approach path is displayed, by a head-up display, on a horizon line with a heading scale. The first straight line represents a ground plot of the approach path. A first assistance gate is displayed such that the first straight line passes through the first assistance gate when the aircraft is aligned on the approach path. A second straight line, parallel with the horizon line and passing through the first point, is displayed and represents a plot on the ground of the origin of the approach path. A second assistance gate is displayed under the horizon line and represents the slope of the approach path.

Abstract: A method of aiding the piloting of an aircraft during a maneuver, bringing about an increase in the attitude of the aircraft, is carried out automatically and repeatedly. According to the method, an attitude deviation is determined by subtracting a first value of attitude from a determined current attitude of the aircraft. A horizon line is presented on a display screen of a head-up display device, superimposed with the environment seen in front of the aircraft, as is an indication of the attitude deviation. The first value of attitude corresponds to the minimum value of (1) an optimal value of attitude at the end of the maneuver and (2) a value of attitude of protection against a rear collision.

Abstract: The invention relates to an avoidance method and system for an aircraft, said avoidance system (1) comprising an anti-collision system (3), calculation means (4) for automatic determination of avoidance instructions, on an alarm, from avoidance information received from the anti-collision system (3) and an avoidance aid system (6, 21), connected to the calculation means (4) which aid the piloting of the aircraft (A), by means of the instructions received from said calculation means (4).

Abstract: An aircraft terrain avoidance method and device may employ a collision warning section that transmits a caution signal when the aircraft risks colliding with the terrain at the end of a first predetermined period of time. A warning signal is transmitted when the aircraft risks colliding with the terrain at the end of a second predetermined period of time, which is shorter than the first predetermined period of time. A piloting system causes the aircraft to automatically climb with a first gradient corresponding to a predetermined value upon the transmission of the caution signal. An automatic pilot is engaged automatically, if currently disengaged, to force the aircraft to climb with a second gradient, corresponding to the maximum gradient possible in the current flight conditions of the aircraft, upon the transmission of the warning signal.

Abstract: Method and device for assisting the lateral control of an aircraft running on a runway. The system (1) comprises a detector (3) for measuring a lateral deviation of the aircraft relative to a lateral alignment beam transmitted by a radio transmitter installed on the ground, the lateral deviation representing an angular deviation between a straight line passing through the radio transmitter and the detector (3) and the centerline of the runway, a calculating means (7) for calculating a first distance which is defined along the runway, between the position of the pilot in the cockpit and the radio transmitter, a central unit (9) for determining from said lateral deviation and said first distance a line intended to correspond with the centerline of the runway, and a head up display device (13) for displaying that line on a display screen (15), superimposed on the environment existing in front of the aircraft, this line being displayed such that it is shown superimposed on said centerline of the runway.

Abstract: Method and system for aiding the piloting of an aircraft, during a maneuver bringing about an increase in the attitude of the aircraft. The system (1) comprises a set (2) of information sources, determining at least one current attitude of the aircraft, a first means (11) for transmitting a first value of attitude which preferably corresponds to the minimum value between, on the one hand, an optimal value of attitude at the end of the maneuver and, on the other hand, a value of attitude of protection against a rear collision, a second means (12) for determining an attitude deviation, by subtracting the first value of attitude from the current attitude, and a head-up display device (5) which is able to present, on a display screen (7), superimposed with the environment, at least one horizon line and a first means of indication which indicates said attitude deviation.

Abstract: A method and a device for assisting the piloting of an aircraft during an approach phase. The piloting aid device comprises a head up display device for displaying, on a display screen (12), a first straight line (13) representing in a true manner the plot on the ground of a first approach path, a first assistance point (25) such that the first straight line (13) passes through this first assistance point (25) when the aircraft is aligned on the first approach path, a second straight line (21) parallel with the horizon (14) and representing in a true manner the plot on the ground of the ending of a second approach path, a second assistance point (23) placed under the horizon line (14) and representing the slop of the second approach path, and a synthetic runway (22) representing in a true manner the plot on the ground of the sides of a landing runway where said first and second approach paths end.

Abstract: Terrain avoidance method and device for an aircraft. The terrain avoidance device (1) comprises a collision warning device (2) capable of transmitting a caution, when the aircraft risks having a collision with the terrain at the end of a first predetermined period of time, and a warning, when the aircraft risks having a collision with the terrain at the end of a second predetermined period of time which is shorter than the said first predetermined period of time, and a piloting system (3) of the aircraft, comprising a means of piloting (4) able to subject the aircraft automatically to a climb command with a first gradient corresponding to a predetermined value, at the time of transmission of a caution, and an automatic pilot which is engaged automatically if it is disengaged and which automatically and exclusively forces the aircraft to climb with a second gradient corresponding to the maximum gradient possible in the current flight conditions of the aircraft, at the time of transmission of a warning.