Abstract: A method and device for aiding piloting of an aircraft during an approach phase for the purpose of landing. The device includes a guidance system for guiding the aircraft according to a first guidance mode during an initial phase upstream of a transition point, then guiding the aircraft according to a second guidance mode during a terminal phase between the transition point and the landing, the device further including a computing system for automatically computing the coordinates of the transition point, the guidance system also configured for automatically disabling the second guidance mode upstream of the transition point.

Abstract: Method and device for automatically managing air operations requiring a guarantee of navigation and guidance performance of an aircraft. The device for automatically managing at least one air operation comprises activatable monitoring of the air operation, a computation unit configured to automatically calculate an anticipated activation point as a function of the application point of the air operation, this anticipated activation point being defined upstream of the application point in the direction of flight of the aircraft, and an activation unit configured to automatically activate monitoring and a display when the aircraft reaches, during its flight, the anticipated activation point.

Abstract: A prediction device for prediction on the ground of characteristics of the position of an aircraft along a path is provided. The prediction device comprises a calculation element comprising a performance and integrity model consistent with a model on board an aircraft. The second calculation element determines precision, integrity and availability information concerning the position of the aircraft along a flight and/or ground path. The integrity information taking account of an integrity of a satellite positioning system and at least one hardware integrity on board the aircraft.

Abstract: Method and device for automatically managing air operations requiring a guarantee of navigation and guidance performance of an aircraft. The device for automatically managing at least one air operation comprises activatable monitoring of the air operation, a computation unit configured to automatically calculate an anticipated activation point as a function of the application point of the air operation, this anticipated activation point being defined upstream of the application point in the direction of flight of the aircraft, and an activation unit configured to automatically activate monitoring and a display when the aircraft reaches, during its flight, the anticipated activation point.

Abstract: The device aids the management of air operations, such as operations under Required Navigation Performance with Authorization Required maneuvers. The device includes a guidance system including a plurality of stages for calculating parameters, each of the stages including an architecture having at least three pieces of equipment, which calculate the parameters and implement monitorings to determine the status of the equipment. The device uses these monitored statuses to determine a global status that indicates if the aircraft is able to carry out the air operations with required performance.

Abstract: A prediction device for prediction on the ground of characteristics of the position of an aircraft along a path is provided. The prediction device comprises a calculation element comprising a performance and integrity model consistent with a model on board an aircraft. The second calculation element determines precision, integrity and availability information concerning the position of the aircraft along a flight and/or ground path. The integrity information taking account of an integrity of a satellite positioning system and at least one hardware integrity on board the aircraft.

Abstract: A monitoring device for automatically monitoring the ability of an aircraft to follow a flight trajectory with at least one turn includes a series of elements that estimate the ability of the aircraft to follow at least one turn of the flight trajectory. For example, a turn radius and limit speed for each of the upcoming turns in a flight plan (or a partial portion of the upcoming turns) are analyzed by comparing to a current speed of the aircraft to determine if there will be any risk of excursion outside the flight plan path, such that warnings can be emitted to a crew of the aircraft to take corrective action before the turns are performed. Consequently, required navigational performance maneuvers can be assured before the beginning of the turns in the flight plan.

Abstract: A method and device for aiding piloting of an aircraft during an approach phase for the purpose of landing. The device includes a guidance system for guiding the aircraft according to a first guidance mode during an initial phase upstream of a transition point, then guiding the aircraft according to a second guidance mode during a terminal phase between the transition point and the landing, the device further including a computing system for automatically computing the coordinates of the transition point, the guidance system also configured for automatically disabling the second guidance mode upstream of the transition point.

Abstract: An assist device for ensuring the accuracy and integrity of position information of an aircraft on the ground includes a processing unit for determining in the airport (AE) a zone (ZP) of insensitivity to multipath GPS signals, the zone (ZP) having a rectangular shape, which is determined relative to the threshold (O) of the runway, and which has a length (L1) equal to the length of the runway and a width (L2) depending on a maximum illumination distance (D). The device further includes a unit for verifying, while the aircraft is moving in the airport (AE), whether the position relative to position information of the aircraft is inside said runway zone (ZP). A method for ensuring the accuracy and integrity of position information of an aircraft on the ground is also disclosed herein.

Abstract: The invention relates to a method for installing an inertial reference unit in an aircraft, in which: a reference unit support (1) is fixed to a structural element of the aircraft; support installation angles—in heading, roll and pitch—representative of angular errors of positioning of the reference unit support relative to an aircraft coordinate system are determined, this determination being based on the measurement of coordinates of points of a previously defined reference coordinate system and of characteristic points of the reference unit support; the said support installation angles are recorded in memory means, for the purposes of subsequent correction of data measured by the inertial reference unit. Preferably the reference coordinate system used is defined by means of targets formed on the structure of a segment of the aircraft for the purposes of joining this segment with an adjacent segment.

Abstract: An assist device for ensuring the accuracy and integrity of position information of an aircraft on the ground includes means for determining in the airport (AE) a zone (ZP) of insensitivity to multipath GPS signals, the zone (ZP) having a rectangular shape, which is determined relative to the threshold (O) of the runway, and which has a length (L1) equal to the length of the runway and a width (L2) depending on a maximum illumination distance (D). The device further includes means for verifying, while the aircraft is moving in the airport (AE), whether the position relative to position information of the aircraft is inside said runway zone (ZP). A method for ensuring the accuracy and integrity of position information of an aircraft on the ground is also disclosed herein.

Abstract: A device calculates a first air speed representing an estimated air speed during flight using measurements of static pressure and total pressure onboard the aircraft. The device includes a storage device for storing in memory, in case of detection of a ground taxiing of the aircraft, the most recently determined value of static pressure corrected from induced aerodynamic effects. As a result, a second air speed representing the estimated air speed during the ground taxiing may be calculated by implementing a correction and using the most recently determined value of static pressure when the ground taxiing of the aircraft is detected. A method for automatically estimating an air speed of an aircraft is also provided.

Abstract: A method and device for optimizing the orientation of a laser anemometer on an aircraft. The device can determine an optimal orientation of a sighting axis of the anemometer and deduce therefrom the orientations of the other sighting axes.

Abstract: A monitoring system including two laser anemometers and a selection logic device able to select, on the one hand, a value of the IAS air speed to be displayed on first display means and, on the other hand, another value of the IAS air speed to be displayed on second display means.

Abstract: Method and device for automatically monitoring the ability of an aircraft to follow a flight trajectory with at least one turn. The monitoring device (1) includes means (6, 8, 10, 11, 14) for implementing monitorings in order to estimate the ability of the aircraft to follow at least one turn of the flight trajectory.

Abstract: The device (1) comprises means for implementing monitorings, and means (5) for determining a global status that indicates if the aircraft is able to carry out air operations with required performance.

Abstract: The device (1) comprises means for registering, in case of detection of a ground taxiing of the aircraft, the last value of static pressure corrected from induced aerodynamic effects.

Abstract: The invention relates to a method for installing an inertial reference unit in an aircraft, in which: a reference unit support (1) is fixed to a structural element of the aircraft; support installation angles—in heading, roll and pitch—representative of angular errors of positioning of the reference unit support relative to an aircraft coordinate system are determined, this determination being based on the measurement of coordinates of points of a previously defined reference coordinate system and of characteristic points of the reference unit support; the said support installation angles are recorded in memory means, for the purposes of subsequent correction of data measured by the inertial reference unit. Preferably the reference coordinate system used is defined by means of targets formed on the structure of a segment of the aircraft for the purposes of joining this segment with an adjacent segment.

Abstract: A method and device for determining anemometric parameters of an aircraft. The device (1) comprises four laser anemometers (A1, A2, A3, A4) that are mounted in pairs (CA, CB) symmetrically on the aircraft and means (4, 5) for determining the angle of sideslip and the angle of incidence of the aircraft, using measurements taken by these laser anemometers (A1, A2, A3, A4).

Abstract: The device (1) comprises means (M1, UC) for determining an optimal orientation of a sighting axis of the anemometer (2) and for deducing therefrom the orientations of the other sighting axes.