Abstract: A device comprises means for computing the air-craft (A) current position means for determining at least one maximum permitted deviation (E1) around a set position of the flight path of the flight plan according to accuracy and integrity performances of said current position computation and to the restriction of a flight range authorised in a flight corridor (6A, 6B), and a display system (7) for displaying at least one a distance scale (9) on a viewing screen (8), at least one a fixed symbol (10) displaying the current position and two movable pointers (13, 14) displaying the limits of said maximum permitted deviation (E1).

Abstract: An aircraft piloting method and device for picking up a vertical profile of a flight plan. The device (1) combines a piloting means (7) enabling a pilot to control the start of the picking-up of a vertical profile, and an automatic piloting means (3) for automatically ending this picking-up, and for following the vertical profile.

Abstract: Device for aiding the piloting of an aircraft during an approach phase for the purpose of landing. The device (1) comprises a guidance system (8) for aiding guidance of the aircraft, in the event of the actuation of a control means (11A, 11B, 11n), both during an initial phase in accordance with a first guidance mode and during a terminal phase in accordance with a second guidance mode, the transition between these first and second guidance modes being achieved automatically by the guidance system (8).

Abstract: The device (1) comprises a set (3) of information sources, an information processing unit (4), a display means (6) comprising a display screen (8), and a configuration means (9) allowing an operator to configure said device (1), according to one of the three configuration states, a first configuration state, for which the display means (6) presents aircraft piloting information, a second configuration state, for which the display means (6) presents aircraft navigation information, and a third configuration state, for which the display means (6) presents both piloting information and navigation information.

Abstract: The invention concerns an approach assisting device (1) comprising a flight management system (2) which determines an approach paths, an inertial reference system (3) which prepares inertial position data, which receives position data of the aircraft, and which determines a hybrid position of said aircraft, a landing assisting multimode receiver (4) which receives data concerning said approach path and said hybrid position, and which deduces therefrom lateral and vertical angular differences, at least when said approach axis is captured, and a guiding system (7) which receives said lateral and vertical angular differences and uses same for guiding the aircraft, at least when said approach path is captured.

Abstract: The device comprises a means for measuring a dynamic temperature on the outside of the aircraft, a means for determining a static temperature around the aircraft, using said dynamic temperature, a means for determining, using said static temperature and a thermodynamic equation, a second temperature value corresponding to an estimated temperature at said destination altitude, a means for determining the difference between said first and second temperature values, and a means for emitting a warning signal when said difference is greater than a predetermined value.

Abstract: The device (1) comprises a computer (9) for computing the difference between at least two items of control information that are generated by at least two different flight management systems of the aircraft, and a system (12) for generating a warning signal if this difference is greater than a threshold value.

Abstract: The method provides for determining an approach mode which has been selected by the pilot of the aircraft from among a plurality of predetermined approach modes, for selecting a characteristic segment (6) of an arrival path which relates to the selected approach mode thus determined, for determining the orientation of the projection on the ground of the said characteristic segment (6) with respect to the center line of the said runway (5) and, depending on this orientation, for determining an anchoring point of the said final approach path, the orientation (?) in a horizontal plane of the said final approach path and the slope (?) of the said final approach path.

Abstract: A method and device for determining a vertical position cue of an aircraft while landing in the presence of a lateral alignment beam, which is emitted from the ground and provides an indication of the aircraft's lateral alignment with respect to a landing strip, may include detecting the lateral alignment beam with aircraft equipment. On the basis of cues relating to the detected lateral alignment beam and of predetermined cues, an axis of approach of the aircraft is determined. Additionally, the actual position and a preset position of the aircraft, which corresponds to the position the aircraft would have if it were on the approach axis, are determined. On the basis of the actual and preset positions of the aircraft, the vertical deviation of the aircraft, representing the vertical position cue, is computed.

Abstract: A method and device for determining a vertical position cue of an aircraft while landing in the presence of a lateral alignment beam, which is emitted from the ground and provides an indication of the aircraft's lateral alignment with respect to a landing strip, may include detecting the lateral alignment beam with aircraft equipment. On the basis of cues relating to the detected lateral alignment beam and of predetermined cues, an axis of approach of the aircraft is determined. Additionally, the actual position and a preset position of the aircraft, which corresponds to the position the aircraft would have if it were on the approach axis, are determined. On the basis of the actual and preset positions of the aircraft, the vertical deviation of the aircraft, representing the vertical position cue, is computed.

Abstract: The device comprises a means for measuring a dynamic temperature on the outside of the aircraft, a means for determining a static temperature around the aircraft, using said dynamic temperature, a means for determining, using said static temperature and a thermodynamic equation, a second temperature value corresponding to an estimated temperature at said destination altitude, a means for determining the difference between said first and second temperature values, and a means for emitting a warning signal when said difference is greater than a predetermined value.

Abstract: Method and device to assist in the piloting of an aircraft in a non-precision approach during a landing phase.

Abstract: The device (1) comprises a set (3) of information sources, an information processing unit (4), a display means (6) comprising a display screen (8), and a configuration means (9) allowing an operator to configure said device (1), according to one of the three configuration states, a first configuration state, for which the display means (6) presents aircraft piloting information, a second configuration state, for which the display means (6) presents aircraft navigation information, and a third configuration state, for which the display means (6) presents both piloting information and navigation information.

Abstract: The method provides for determining an approach mode which has been selected by the pilot of the aircraft from among a plurality of predetermined approach modes, for selecting a characteristic segment (6) of an arrival path which relates to the selected approach mode thus determined, for determining the orientation of the projection on the ground of the said characteristic segment (6) with respect to the center line of the said runway (5) and, depending on this orientation, for determining an anchoring point of the said final approach path, the orientation (&agr;) in a horizontal plane of the said final approach path and the slope (&bgr;) of the said final approach path.