Abstract: A flight management system of an aircraft is provided allowing notably the calculation of a trajectory over the terrestrial globe. The calculation of a trajectory is carried out with respect to a true North, true North being a navigation term referring to the direction of the geographical North pole with respect to a given position. When the current or estimated position of the aircraft is level with the pole, it then becomes impossible to define true North, true North being defined in all the directions or in no direction, depending on the calculation facilities used. The flight management system makes it possible to use a single calculation procedure whatever the current position or the position to be reached of the aircraft on the terrestrial globe.

Abstract: A flight management system of an aircraft is provided allowing notably the calculation of a trajectory over the terrestrial globe. The calculation of a trajectory is carried out with respect to a true North, true North being a navigation term referring to the direction of the geographical North pole with respect to a given position. When the current or estimated position of the aircraft is level with the pole, it then becomes impossible to define true North, true North being defined in all the directions or in no direction, depending on the calculation facilities used. The flight management system makes it possible to use a single calculation procedure whatever the current position or the position to be reached of the aircraft on the terrestrial globe.

Abstract: The present invention relates to a method of generating instruction values for servo-controlling a flight parameter P of an aircraft equipped with an automatic pilot, between a current value C and a target value T. It comprises a phase for determining increasing or decreasing instruction values PC of the flight parameter P and instruction values ( ? P ? t ) C of its time derivative and/or (?Pdt)C of its integral. It also comprises a phase of use, by a servo-control law of the parameter P of the automatic pilot, of each of the instruction values PC, ( ? P ? t ) C and/or (?Pdt)C. It also comprises a phase of use, by the automatic pilot, of the value T as final target value. The instruction values PC, ( ? P ? t ) C and/or (?Pdt)C are calculated from the current value C, the target value T of the parameter P and a time constant ?.

Abstract: The present invention relates to compliance, by the FMS flight management computer equipping an aerodyne, with a constraint, in particular an altitude constraint, of the flight plan (Dpv) at an imposed waypoint close to the position of the aerodyne at the moment of instigation of its automatic flight plan following function. It consists in validating in advance such a constraint by projecting itself into a near future by means of a forecast (Pt) of the displacement of the aerodyne taking account of the motion of the aerodyne during the transition between the instances of application of the flight presets prevailing before the instigation of the automatic following function and those newly provided by the FMS flight computer (30) during this instigation.