Thales

Benoit Dacre-Wright

Guy Deker

François Coulmeau

Xavier Blanchon

Vincent Savarit

Christophe Pierre

Didier Poisson

Rémy Auletto

Mathieu Le Merrer

A method is provided for adjusting a flight plan rejoining trajectory of an aircraft, the method being implemented in a flight management system of the aircraft. In a first step, the rejoining trajectory comprises a guidance setpoint holding point to be reached situated in the extension of a guidance setpoint, and set manually or automatically, the guidance setpoint no longer being necessarily maintained when this setpoint holding point is passed. This first step can be preceded by a step of rejoining a guidance setpoint or a step of searching for the intersection of the current guidance setpoint trajectory with a segment of the flight plan.

Rejoining trajectory adjustment method for aircraft

A method assisting in navigation of aircraft following a flight plan subject to time constraints comprises: determining a minimum speed profile, a maximum speed profile, and minimum and maximum times of passage; determining, for each constraint of index i, a restricted interval and a required interval; the determination made by a first iterative computation, i being decremented from n&#x2212;1 to 1 and comprising: determining a required interval of index i enabling the aircraft to observe a restricted interval of index i+1 by flying at a speed profile between the minimum and maximum speed profiles, the restricted interval of index i+1 determined on the preceding iteration for an iteration of index between 1 and n&#x2212;2, or from the time constraint of index n for the iteration of index n&#x2212;1; and determining a restricted interval of index i from the intersection of the time constraint and the required interval of index i.

Navigation aid method for making multiple time constraints

A method for computing a setpoint trajectory of an aircraft comprising at least two subsets comprises the formulation and the solving of an optimization problem for the trajectory, and the formulation of the problem comprises at least the formulation of a constraint related to a transition of legs on at least one first subset of the trajectory, and the formulation of a constraint related to a transition of vertical flight phases on at least one second subset of the trajectory. The invention also relates to a system and a computer program for the computation of a trajectory.

Method of computing aircraft trajectory subject to lateral and vertical constraints

A navigation aid method for an aircraft flying a reference trajectory between a point of departure and a point of arrival subject to a field of wind vectors comprises: decomposing the reference trajectory into a plurality of discrete waypoints Pi, loading meteorological data comprising the field of wind vectors, iterating the following steps N times, to generate an improved trajectory: for each waypoint Pi named current point, determining a reference plane, determining an orthonormal reference frame, determining a wind curl ((&#x2207;W)), determining a sign of the projection of the wind curl on axis zi ((&#x2207;W)), determining a direction of displacement from the current point Pi to a new current waypoint Pi', determining a line of displacement, determining a displacement distance, determining the new current waypoint, determining a new trajectory, assigning the new waypoints Pi&#x2032; determined in the preceding iteration to the waypoints Pi for the next iteration.

Navigation aid method based on meteorological conditions

A method is provided for guaranteeing a temporal spacing between an aircraft and at least one reference moving object, said spacing needing to be guaranteed no later than at a point in the flight plan called the point of interception, with the aircraft following a current flight plan. The feasibility of guaranteeing the spacing at a date Tcour by regulating the speed of the aircraft while maintaining the current flight plan is verified in a first step. In a second step it is verified whether the date Tcour is contained within a feasibility range. In a third step the current flight plan is modified when the feasibility is not verified, a lateral trajectory between the current position Xcour of the aircraft and the point of interception being implemented in this case such that the spacing can be attained by regulating the speed.

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Lauzerville, France

Benoit Dacre-Wright