Abstract: A method for determining a result path of an aircraft, the result path including a set of successive positions of the aircraft between an initial global point and a final global point that are predetermined for a mission of the aircraft is provided. The aircraft includes a plurality of calculating members, each able to guide the aircraft during at least part of the mission and to calculate an elementary path of the aircraft during that part, each elementary path including a set of successive positions of the aircraft between an initial elementary point and a final elementary point. The device includes calculating a portion of the result path from elementary paths coming from at least two distinct calculating members.

Abstract: A graphic interaction method for piloting an aircraft, comprises receiving an indication of an object selected on a display screen of the aircraft; determining one or more flight plan revisions of the aircraft associated with the selected object and displaying one or more of said flight plan revisions; receiving an indication of selection of a displayed revision; determining a revision type associated with the revision displayed and selected; and as a function of the revision type determined, displaying a tactile interface data entry graphic symbol. Developments notably concern the symbology used, the validation or the modification of a selected revision, the taking account of the flight context, the taking account of the speed of manipulation of the tactile interface, etc. System and software aspects are described. In particular, the human-machine interface may be exclusively of tactile type.

Abstract: The trajectory coming from a planned trajectory, managed by a system, and from at least one trajectory section sent by a third party system to the system, the method at least comprises: a preliminary step in which a knowledge base is produced comprising the calculation parameters and their field of use for the moving object, several envelopes of parameters being defined within the field of use corresponding to different operational constraints of the moving object; a first step in which the system initializes the planned trajectory according to the parameters of the preliminary step, the calculation parameters of the planned trajectory being contained in one of the envelopes; a second step in which the system receives a trajectory section sent by the third party system in order to be inserted in the planned trajectory by replacing a part of the trajectory; a third step in which the received and accepted section is simplified by segmentation in such a way that its calculation parameters are contained in the at

Abstract: A method of graphical manipulation of the trajectory of an aircraft comprises the steps of receiving an indication of a deformation point associated with the trajectory of the aircraft; determining a zone of local modification of the trajectory of the aircraft as a function of the deformation point; computing a modified trajectory and graphically restoring the modified trajectory. A parameter associated with the indication of the deformation point, notably a speed and/or acceleration value (for example of the contact point on the touch-sensitive interface, or else of a cursor), is received or determined. A modified trajectory is computed by selecting a computation algorithm from among a plurality of faster or slower predefined algorithms; the selection being performed as a function of the parameter. Various other developments are described (configurable selection, trajectory modification bounds, processing of an arbitrary deformation point, i.e. one other than a point of the flight plan, etc.).

Abstract: The system executes services by an application called “server” for at least one application called “client.” A preliminary step establishes for each service a list of calculation parameters that can be varied in a given range, called “adjustable parameters” as well as time and quality of the said service information according to the value of the said parameters. At the request of a client for a given service, the method adjusts the value of the adjustable calculation parameters as a function of a given constraint, the service being executed using the adjusted values of the said parameters.

Abstract: The invention relates to a method for formulating the strategy of an aircraft, with a view to favouring adherence to a time constraint. With this aim, the method according to the invention consists in optimizing the margin available for the formulation of the aircraft's speed strategy, by calculating a first target required time of arrival (RTAtarget) which is higher, respectively lower, than the required time of arrival (RTA), in the case where said required time of arrival (RTA) is greater, respectively less, than the mean estimated time of arrival (ETAmean). According to the invention, the first target required time of arrival (RTAtarget) is used for the formulation of the aircraft's speed strategy. According to the invention, a second target required time of arrival (RTAtarget2) can be determined subsequently, and used for the formulation of the speed strategy, with the aim of utilizing the margin, previously optimized, available for the formulation of the aircraft's speed strategy.

Abstract: A method implemented by computer for the display of information relating to the flight of an aircraft comprises receiving indication of a selection of an arbitrary display zone on a screen of an onboard computer of the aircraft; and reconfiguring the display, in response to the indication. Developments describe several geometric transformations, various display reconfigurations (e.g. centring of the display), the use of systems third party to the aircraft (e.g. taxiing computer, ground client, maintenance, terrain monitoring, traffic, weather), associated operations of revisions of the flight plan, the use of display rules (notably associated with the flight situation), and the emergency deactivation of the display reconfigurations. Computer programs and associated systems are also described (notably Man-System Interface, virtual and/or augmented reality).

Abstract: A system executes services by a “server” for a “client”. A preliminary step establishes a list of available services of the server, set up for the client, in which a processing time is determined releasable by the server for the client per code execution cycle MIF. The system creates on start-up: NT execution tasks for the client, each having a priority of execution level and an allocated average duration of execution, NT being at least 1, the sum of durations of the tasks being at most the releasable processing time; execution rules associating each of the tasks with at least one service of the list; then, during each MIF cycle, the system executes the services on their associated tasks, a task executed by priority and for at most its allocated average time of execution, the non-executed part of a service being executed on its associated task in the next cycle.

Abstract: A method for assisting the navigation of an aircraft comprises: assembly by families of data by a processing unit of predetermined data and acquired data, including meteorological data, the families being predefined, each data value being associated with a time window of validity; formatting the data of the families to associate with each data value a type of graphical representation as text or a scalar, vector, surface, or volume; selection of families of data to be displayed; choice of a display time window for each family of data to be displayed; spatio-temporal discretization of the trajectory; spatio-temporal correlation of the discretized trajectory with each family of data as a function of the time windows of validity, in the display time windows of the family, to extract a sub-assembly from each family of data, by the processing unit; display of the sub-assemblies in a single representation on the same display screen.

Abstract: A method for aiding navigation for an aircraft between a descent start point and a computation end point, comprises the computation steps of: collecting a flight plan consisting of a succession of waypoints and of the associated vertical constraints; determining a corridor consisting of a floor trajectory and of a ceiling trajectory defining the minimum and maximum altitudes permitted to the aircraft; splitting the corridor into several cells defined between two waypoints furthest apart and between which the ceiling trajectory is distinct from the floor trajectory; determining for at least one cell a vertical trajectory complying with the altitude constraints and comprising the longest possible IDLE segment; and a step consisting in determining and displaying maneuvering points of the aircraft making it possible to follow the target vertical trajectory.

Abstract: A method is provided for managing the flight of an aircraft flying a trajectory calculated by a flight management system. The trajectory necessitates at least one transition between two different aerodynamic configurations of the aircraft. The method comprises: extraction of performance data of the aircraft from a database, at least one item of performance data being a function of an aerodynamic configuration, selection between a first determination step and a second determination step, a step of determination of a start point and of an end point of the transition between two aerodynamic configurations and engine speeds of an aircraft during a flight, the determination step being implemented by the flight management system and chosen from among the first and second determination steps, the determination step calculating the trajectory by numerical integration of the equations representative of the dynamics of the aircraft making use of the performance data of the aircraft.

Abstract: The method concerns monitoring the approach phase of an aircraft to a runway. This method includes determining successive gateways of the aircraft relative to at least one characteristic point of an approach flight plan of the aircraft or relative to the landing location, and measuring the aircraft speed upon crossing a given gateway. The method further comprises computing a minimum deceleration distance up to a predetermined target speed associated with the gateway following said given gateway, the minimum deceleration distance being an estimated flight distance corresponding to the speed reduction of the aircraft from the measured speed to said target speed; comparing the computed minimum deceleration distance with the distance remaining to be flow to the following gateway; and generating an alert, intended for the aircraft crew, when the distance remaining to be flown to the following gateway is smaller than the computed minimum deceleration distance.

Abstract: A device and method for assisting with reconfiguration of an aircraft, an aircraft including such a device and an associated computer program product are disclosed. In one aspect, the aircraft has an operational configuration, is configured to move in an operational environment, and includes at least one avionic system, at least one avionic member, and at least one monitoring system configured to detect an abnormality of an avionic member or a perturbation of the operational environment and to generate a fault information. The device is connected between at least one monitoring system and at least one avionic system, and includes a reception module configured to receive a fault information from the monitoring system, an impact computation module configured to compute an impact on the operational configuration of the aircraft, and a transmission module configured to transmit the computed impact to at least one avionic system.

Abstract: A method for determining a result path of an aircraft, the result path including a set of successive positions of the aircraft between an initial global point and a final global point that are predetermined for a mission of the aircraft is provided. The aircraft includes a plurality of calculating members, each able to guide the aircraft during at least part of the mission and to calculate an elementary path of the aircraft during that part, each elementary path including a set of successive positions of the aircraft between an initial elementary point and a final elementary point. The device includes calculating a portion of the result path from elementary paths coming from at least two distinct calculating members.

Abstract: A supervision device for an aircraft including a plurality of avionics systems, each avionics system being able to generate parameters representative of its operation on a reference date, includes a plurality of prediction modules, each prediction module including a computer for computing projections representative of the trajectory of the aircraft and/or representative of the operation of at least one avionics system on a corresponding prediction date, the prediction date being after the reference date, at least one projection computed by a prediction module depending on at least one other projection computed by another prediction module.

Abstract: A method for aiding navigation for an aircraft between a descent start point and a computation end point, comprises the computation steps of: collecting a flight plan consisting of a succession of waypoints and of the associated vertical constraints; determining a corridor consisting of a floor trajectory and of a ceiling trajectory defining the minimum and maximum altitudes permitted to the aircraft; splitting the corridor into several cells defined between two waypoints furthest apart and between which the ceiling trajectory is distinct from the floor trajectory; determining for at least one cell a vertical trajectory complying with the altitude constraints and comprising the longest possible IDLE segment; and a step consisting in determining and displaying maneuvering points of the aircraft making it possible to follow the target vertical trajectory.

Abstract: A method is provided for managing the flight of an aircraft flying a trajectory calculated by a flight management system. The trajectory necessitates at least one transition between two different aerodynamic configurations of the aircraft. The method comprises: extraction of performance data of the aircraft from a database, at least one item of performance data being a function of an aerodynamic configuration, selection between a first determination step and a second determination step, a step of determination of a start point and of an end point of the transition between two aerodynamic configurations and engine speeds of an aircraft during a flight, the determination step being implemented by the flight management system and chosen from among the first and second determination steps, the determination step calculating the trajectory by numerical integration of the equations representative of the dynamics of the aircraft making use of the performance data of the aircraft.

Abstract: A method for assisting in the navigation of an aircraft comprises steps of calculating and displaying a linear deviation on a first linear section and an angular deviation on a second angular section. The method comprises a step of calculation of an anticipated deviation of the aircraft, expressed linearly or angularly, projected to a time DT, characteristic of a reaction time of the aircraft, and of a statistical error distribution associated with this anticipated deviation; and a step of calculation of a probability of exceeding a predetermined target deviation, by means of the anticipated deviation and of the statistical error distribution. The method also comprises a crew alert when the probability is above a predetermined threshold.

Abstract: A method and device for determining a shifted circular segment on the basis of an initial circular segment, the shifted circular segment being shifted by a shift distance, the method being implemented by a computer dedicated to flight management, comprises: determining a shifted final point terminating a shifted circular segment, on the basis of the final point terminating the initial circular segment, through a shift of the final point determined on the basis of the shift distance and in the direction of shift, through the use of a straight line passing through the center of the initial circular segment and the final point of the initial circular segment, and determining a shifted circular segment on the basis of the initial circular segment by construction of a circular segment between the shifted final point associated with the preceding shifted segment and the shifted final point associated with the shifted segment.

Abstract: A method for assisting in the navigation of an aircraft comprises steps of calculating and displaying a linear deviation on a first linear section and an angular deviation on a second angular section. The method comprises a calculation step for converting an angular deviation into an equivalent linear deviation, and, conversely, converting a linear deviation into an equivalent angular deviation. The method comprises a step of graphic representation, called unified monitoring, intended for the crew, of a deviation of the aircraft, on a lateral deviation axis and a vertical deviation axis; each of the deviations, lateral and vertical, being able to be represented on a linear scale, an angular scale or a mixed scale.