Abstract: Disclosed is a method and device for assisting guidance of an aircraft. A flight management system is used to determine guidance instructions that include speed instructions having at least one flight time constraint to guide the aircraft to a check-point. An accuracy level for complying with the flight time constraint and at least one error level for at least one flight parameter are generated by an accuracy generating unit. An operating margin for at least one second parameter is determined from the determined accuracy and error levels, with the operating margin being representative of air speed criterion values of the aircraft. A range determining unit is used to determine whether the range of air speed criterion values is within an air speed envelope of the aircraft, and the speed instructions are modified when the range of air speed criterion values is not within the air speed envelope.

Abstract: A method and device for servocontrolling an aircraft speed-wise in an approach phase. The device can adapt to the estimated time of passage of the aircraft at a particular point of the approach trajectory, the position of the start of deceleration of the aircraft in the approach phase.

Abstract: The inventive flight control assisting device comprises first means (4) for determining the actual aircraft flight conditions, second means (5) for determining, with the aid of said actual flight conditions and a predetermined pattern, a minimum approaching distance corresponding to a minimum distance between projections on the horizontal plane of the aircraft actual position and a touch-down point when said aircraft moves downwards and decelerates according to an optimised approach in such a way that stabilised approaching conditions are attained, and display means (7) for displaying at least said minimum approaching distance on a navigation screen (9) in the form of a first circular arc focused on a position relative to the aircraft which displays the touch-down position.

Abstract: Method and device for aiding the guidance of an aircraft along a flight trajectory. The device makes it possible to cause the aircraft to pass at least one particular waypoint of the flight trajectory, at an associated target time, and to do so to within an associated temporal tolerance.

Abstract: Disclosed is a method and device of guiding an aircraft along a flight trajectory to comply with a time constraint for arriving at a required arrival time at a waypoint of the flight trajectory. Speed setpoints are determined according to a speed profile that complies with the required arrival time at the waypoint, based on estimated values of parameters relating to the flight of the aircraft, and by taking account of an upper limit for a maximum speed at which the aircraft flies along the flight trajectory. The determined speed setpoints are applied to the aircraft during guidance of the aircraft along the flight trajectory.

Abstract: A method and device for aiding the piloting of an aircraft while respecting a time of arrival constraint at a first waypoint during a phase of descent. The method includes calculating an instant of arrival of the aircraft at an intermediate waypoint, in such a way that an estimated latest time of arrival at the first waypoint, corresponding to a minimum speed profile, occurs later by a predetermined first margin than the time of arrival constraint; determining a first speed profile between a current position of the aircraft and the intermediate waypoint, such that the intermediate waypoint is crossed at the calculated instant of arrival; determining a second speed profile, such that the first waypoint is crossed within the time of arrival constraint, starting from the intermediate waypoint at the calculated instant of arrival; and piloting the aircraft according to the first and then second speed profiles.

Abstract: The guidance system (1) comprises a first means (2) for guiding the aircraft while maintaining a spacing with another aircraft, a second means (3) for making the aircraft pass through a particular waypoint at a required passing time, and means (5) for selecting automatically one of said first and second means (2, 3).

Abstract: Disclosed is a method and device for automatically guiding separation of a follow aircraft from a lead aircraft. The method involves determining first guidance instructions based on a speed that enables a desired separation between the lead and follow aircraft, and determining second guidance instructions based on a speed for performing a desired landing procedure for the follow aircraft. A current energy state of the follow aircraft is monitored to detect an incompatibility situation in which the current energy state of the follow aircraft is incompatible with execution of the desired landing procedure.

Abstract: An aircraft guidance device includes a flight computer that formulates all guidance orders for the aircraft, irrespective of a selected guidance mode.

Abstract: A guidance system includes a device to generate an alphanumeric identification characteristic, enabling identification of a data item which is used for a selected guidance mode of an aircraft. The system also includes a display unit which automatically shows the alphanumeric identification characteristic on a display screen.

Abstract: A method for detecting an error in input of one of the takeoff parameters into a flight management system includes a step of calculating a limit value based on one or more takeoff parameters input into the flight management system. The method further includes a step of comparing the calculated limit value with characteristic takeoff values.

Abstract: The guidance device (1) comprises a flight computer (7) which comprises means (15) for formulating all the guidance orders for the aircraft, irrespective of the guidance mode selected.

Abstract: A method and device for servocontrolling an aircraft speed-wise in an approach phase. The device (1) comprises means (15, 16, 17) for adapting to the estimated time of passage of the aircraft at a particular point of the approach trajectory, the position of the start of deceleration of the aircraft in the approach phase.

Abstract: The inventive flight control assisting device comprises first means (4) for determining the actual aircraft flight conditions, second means (5) for determining, with the aid of said actual flight conditions and a predetermined pattern, a minimum approaching distance corresponding to a minimum distance between projections on the horizontal plane of the aircraft actual position and a touch-down point when said aircraft moves downwards and decelerates according to an optimised approach in such a way that stabilised approaching conditions are attained, and display means (7) for displaying at least said minimum approaching distance on a navigation screen (9) in the form of a first circular arc focused on a position relative to the aircraft which displays the touch-down position.

Abstract: A system for aiding the piloting of an aircraft during a runway approach includes an information source that provides information relating to the aircraft and its environment. A computation unit determines, with the aid of information provided by the information source, an energy reference profile having a trajectory reference profile and a speed reference profile that allows the aircraft to regain a stabilized approach trajectory, if it follows the reference profile. A monitor verifies that the aircraft is following the reference profile. An indicator supplies the pilot with piloting indications for piloting the aircraft so as to follow the reference profile.

Abstract: The device (1) comprises means (4) for determining speed setpoints making it possible to guide the aircraft so that it arrives at a particular waypoint at a time corresponding to a time constraint, by taking account of an upper speed limit for a current flight stretch and of an auxiliary upper speed limit for a distant flight stretch.

Abstract: The device (1) comprises means (2) for automatically determining first instructions enabling the aircraft to follow another aircraft with a particular separation, means (3) for automatically determining second instructions making it possible to perform a landing procedure, and means (6, 9) for automatically applying to the aircraft said first instructions or said second instructions according to its energy state.

Abstract: A method and device for aiding the piloting of an aircraft while respecting a time of arrival constraint at a first waypoint during a phase of descent. The method includes calculating an instant of arrival of the aircraft at an intermediate waypoint, in such a way that an estimated latest time of arrival at the first waypoint, corresponding to a minimum speed profile, occurs later by a predetermined first margin than the time of arrival constraint; determining a first speed profile between a current position of the aircraft and the intermediate waypoint, such that the intermediate waypoint is crossed at the calculated instant of arrival; determining a second speed profile, such that the first waypoint is crossed within the time of arrival constraint, starting from the intermediate waypoint at the calculated instant of arrival; and piloting the aircraft according to the first and then second speed profiles.

Abstract: The guidance system (1) comprises means (2, 6) for generating an alphanumeric identification characteristic, making it possible to identify a data item which must be used for a selected guidance mode of the aircraft, and display means (10) which automatically shows this alphanumeric identification characteristic on a display screen (12).

Abstract: The device (1) comprises means (4, 7) for determining guidance instructions making it possible to guide the aircraft so that it passes a particular check-point at a time corresponding to a time constraint, taking into account an accuracy level relating to this time constraint and an error level for at least one parameter which is used in calculating said guidance instructions.