Abstract: The guidance device of the aircraft includes a unit for constructing a flight trajectory of the aircraft, which adapts the height of the flight trajectory to a downstream relief so as to allow the aircraft to clear this downstream relief by implementing a rectilinear climb at maximum rate of climb of the aircraft, along a rectilinear lateral direction corresponding to the direction of the aircraft at the moment of the triggering of the maneuver.

Abstract: A calculation unit configured to define a safety corridor, whose width is increased compared with a nominal width, at least by one width of an escape trajectory with a spiral climb of the aircraft, wherein the safety corridor that is thus defined by the calculation unit is used by a construction unit for forming a flight trajectory for a low level flight of an aircraft.

Abstract: The guidance device of the aircraft includes a unit for constructing a flight trajectory of the aircraft, which adapts the height of the flight trajectory to a downstream relief so as to allow the aircraft to clear this downstream relief by implementing a rectilinear climb at maximum rate of climb of the aircraft, along a rectilinear lateral direction corresponding to the direction of the aircraft at the moment of the triggering of the maneuver.

Abstract: A calculation unit configured to define a safety corridor, whose width is increased compared with a nominal width, at least by one width of an escape trajectory with a spiral climb of the aircraft, wherein the safety corridor that is thus defined by the calculation unit is used by a construction unit for forming a flight trajectory for a low level flight of an aircraft.

Abstract: The device (1) comprises a first system (3) which comprises means (14) for calculating the vector difference between a position generated by this first system (3) and a realignment position received from a second system (4), for one and the same date-stamping, and means (16) for adding this difference to any new position of the aircraft, generated by said first system (3), so as to obtain each time a realigned position.

Abstract: A process for transmitting data between at least one display screen in a cockpit and at least one remote client system includes at least one computer, in which the display screen displays a first request to send a message in a first communication protocol; this message is sent to the remote client system over a first link using a second communication protocol. A request to confirm a message is generated and displayed on the display screen via a communication interface designed to receive and generate messages in this first communication protocol and to receive and generate messages that can be received by the remote client system.

Abstract: A process for transmitting data between at least one display screen in a cockpit and at least one remote client system includes at least one computer, in which the display screen displays a first request to send a message in a first communication protocol; this message is sent to the remote client system over a first link using a second communication protocol. A request to confirm a message is generated and displayed on the display screen via a communication interface designed to receive and generate messages in this first communication protocol, and to receive and generate messages that can be received by the remote client system.

Abstract: The device (1) comprises a first system (3) which comprises means (14) for calculating the vector difference between a position generated by this first system (3) and a realignment position received from a second system (4), for one and the same date-stamping, and means (16) for adding this difference to any new position of the aircraft, generated by said first system (3), so as to obtain each time a realigned position.