Abstract: This electronic device for storing a terrain database for an avionics system is carried on board an aircraft. The terrain database corresponds to a terrain zone likely to be overflown by the aircraft, represented in the form of a surface area divided into meshes, each mesh corresponding to a sector of the terrain zone, the terrain database having a first resolution and comprising first terrain elevation values, each associated with a respective mesh. The terrain database further comprises, for each mesh, an uncertainty value associated with the respective first elevation value, at least one uncertainty value being calculated from a plurality of second terrain elevation values associated with said mesh and from a second terrain database having a second resolution higher than the first resolution.

Abstract: A method for generating at least one trajectory element (T) for controlling an aircraft (1) according to the trajectory element (T), the generation method being at least partially implemented by a generation system (2) on board the aircraft (1), and comprising the steps of: receiving a first initial data stored in a first database (6), the first database (6) presenting a first predefined level of integrity, called the initial level of integrity; receiving a second initial data stored in a second database (8), the second database (8) presenting said initial level of integrity, the first database (6) being dissimilar relative to the second database (8); comparing at least one first trajectory data (D1) with at least one second trajectory data (D2); obtaining the trajectory element (T).

Abstract: The invention relates to a method for validating at least one position stored in a database of an aircraft comprising a satellite positioning system, the database containing at least one radionavigation beacon position, a runway threshold position, and a displaced runway threshold position on a runway, on which the aircraft is intended to land, the validation of said at least one position comprising a consistency check between at least: a signal received by the aircraft from a radionavigation beacon associated with said at least one position, and the position of the aircraft provided by the satellite positioning system, and the value of the position stored in the database.

Abstract: Disclosed is a method of guiding the pilot of an aircraft for the alignment maneuver, including: determining at a first instant an occurrence close to the alignment maneuver and triggering the display of a first symbol on the screen; updating the position of the first symbol on the horizon according to the updated value of the aircraft heading; when the alignment maneuver is to begin, moving a second symbol on the screen from the position of the first symbol, the direction of the displacement with respect to the horizon being determined depending on the direction of the crosswind with respect to the runway and the value of the displacement being determined depending on the difference between the current dynamic sideslip of the aircraft and a current dynamic sideslip setpoint value calculated for the aircraft.

Abstract: Method and device for assisting with landing an aircraft under poor visibility conditions are provided. The method allows sensor data to be received during a phase of approach toward a runway when the runway and/or an approach lighting system are not visible to the pilot from the cockpit; then, in the received sensor data, data of interest characteristic of the runway and/or the approach lighting system to be determined; then, on the basis of the data of interest, the coordinates of a target area to be computed; and, on a head-up display, a guiding symbol representative of the target area to be displayed, the guiding symbol being displayed before the aircraft reaches the decision height, in order to provide the pilot with a visual cue in which to search for the runway and/or approach lighting system.

Abstract: Electronic device for estimating a position of an air traffic element intended to be carried on board an aircraft, and comprising a module for acquiring a measured position of the air traffic element and complementary measured navigation information of the air traffic element; and a module for calculating an estimated position of the air traffic element. The calculation module is configured to calculate the estimated position of the air traffic element as a function of the measured position and of the complementary measured navigation information acquired for the air traffic element. The complementary measured navigation information is preferably a measured position of the complementary air traffic element, or a set of at least two measured positions of the complementary air traffic element, or even a measured speed of the air traffic element.

Abstract: This method for determining a virtual speed vector includes the steps of acquiring (110) a sequences of images of the surrounding environment from an image sensor defining an optical projection center that is substantially stationary relative to the mobile engine, analyzing (120) at least two successive images in order to determine, in each of the two images, a point, called epipole, representing the position in said image of the optical center of the image sensor at the moment of the acquisition of the other image, and for each analyzed image, determining (130) the position of the epipole of said image on a display usable to pilot the mobile engine and displaying (130), on the display, a symbol representative of the virtual speed vector in said position.

Abstract: A method of calculating a speed of an aircraft, a method for calculating a protection radius, a positioning system and an associated aircraft are disclosed. In one aspect, the method includes obtaining a measured speed of the aircraft and obtaining a measured position of the aircraft, associated with a reliability protection radius related to position. The method also includes calculating, by a correction loop, a corrected speed, wherein the calculation of the corrected speed includes calculating a calculated position by integration of the corrected speed, and correcting the measured speed as a function of a difference between the calculated position and the measured position. The method further comprising calculating a reliability protection radius related to the corrected speed.

Abstract: The invention relates to a method for validating at least one position stored in a database of an aircraft comprising a satellite positioning system, the database containing at least one radionavigation beacon position, a runway threshold position, and a displaced runway threshold position on a runway, on which the aircraft is intended to land, the validation of said at least one position comprising a consistency check between at least: a signal received by the aircraft from a radionavigation beacon associated with said at least one position, and the position of the aircraft provided by the satellite positioning system, and the value of the position stored in the database.

Abstract: 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: an image sensor configured to acquire environmental images during the path traveled by the device; an image processing module capable of determining the drift of the device in real time; a module for determining information that is representative of the route taken by the device, a module for real-time determination of the true heading followed by the device from the information that is representative of the route and the drift of the device, a module for returning to the user information that is representative of the true heading.

Abstract: This method for determining a virtual speed vector includes the steps of acquiring (110) a sequences of images of the surrounding environment from an image sensor defining an optical projection center that is substantially stationary relative to the mobile engine, analyzing (120) at least two successive images in order to determine, in each of the two images, a point, called epipole, representing the position in said image of the optical center of the image sensor at the moment of the acquisition of the other image, and for each analyzed image, determining (130) the position of the epipole of said image on a display usable to pilot the mobile engine and displaying (130), on the display, a symbol representative of the virtual speed vector in said position.

Abstract: 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: an image sensor configured to acquire environmental images during the path traveled by the device; an image processing module capable of determining the drift of the device in real time; a module for determining information that is representative of the route taken by the device, a module for real-time determination of the true heading followed by the device from the information that is representative of the route and the drift of the device, a module for returning to the user information that is representative of the true heading.

Abstract: The general field of the invention is that of the methods for three-dimensional graphic representation of at least one landing runway on a display device of an onboard display system for aircraft, said graphic representation being displayed in a synthetic of an outside landscape, said runway comprising a coloured rectangular form, an outline surrounding said form and markings the position of the aircraft in relation to said runway being known in a horizontal plane with a first accuracy and in a vertical axis with a second accuracy. When the first accuracy is above a first threshold and/or when the second accuracy is above a second threshold, the appearance of the rectangular form or of the outline or of at least one marking is modified.

Abstract: A method of calculating a speed of an aircraft, a method for calculating a protection radius, a positioning system and an associated aircraft are disclosed. In one aspect, the method includes obtaining a measured speed of the aircraft and obtaining a measured position of the aircraft, associated with a reliability protection radius related to position. The method also includes calculating, by a correction loop, a corrected speed, wherein the calculation of the corrected speed includes calculating a calculated position by integration of the corrected speed, and correcting the measured speed as a function of a difference between the calculated position and the measured position. The method further comprising calculating a reliability protection radius related to the corrected speed.

Abstract: The general field of the invention is that of the methods for three-dimensional graphic representation of at least one landing runway on a display device of an onboard display system for aircraft, said graphic representation being displayed in a synthetic of an outside landscape, said runway comprising a coloured rectangular form, an outline surrounding said form and markings, the position of the aircraft in relation to said runway being known in a horizontal plane with a first accuracy and in a vertical axis with a second accuracy. When the first accuracy is above a first threshold and/or when the second accuracy is above a second threshold, the appearance of the rectangular form or of the outline or of at least one marking is modified.

Abstract: A receiver of a digital signal equipped with an N-state weighted-decision trellis Viterbi decoder, the signal received including a series of symbols, is provided. The receiver comprises a programmable logic circuit that includes a source memory A and a destination memory B each comprising N rows and M+L columns respectively allocated to M fixed fields for describing the trellis, and to L variable fields, and an operator able to calculate the variable fields of a memory as a function of the fixed fields of the said memory, of the symbols received and of the variable fields of the other memory and able to reverse the role of the source memory and destination memory.

Abstract: A multifrequency receiver comprises a first receiving subsystem comprising: means for receiving at least a first and a second distinct frequency at least one of which comprises a signal containing information relating to the position of a satellite, the said receiving means comprising: a first amplification stage delivering a first filtered signal based on the signal received by the receiver; a second stage for processing each of the received frequencies; a third stage comprising a mixer and at least one local oscillator; and a fourth amplification and filtering stage making it possible to amplify the filtered signal at the output of the mixer. The second stage comprises: a first switch; means for amplifying the signals of the two channels; and a second switch making it possible to deliver the signal to the third stage.

Abstract: A receiver of a digital signal equipped with an N-state weighted-decision trellis Viterbi decoder, the signal received including a series of symbols, is provided. The receiver comprises a programmable logic circuit that includes a source memory A and a destination memory B each comprising N rows and M+L columns respectively allocated to M fixed fields for describing the trellis, and to L variable fields, and an operator able to calculate the variable fields of a memory as a function of the fixed fields of the said memory, of the symbols received and of the variable fields of the other memory and able to reverse the role of the source memory and destination memory.