Abstract: A configured aircraft flight management aid system comprises: means of interpretation receiving data taken from external instructions from an external control center, data relating to aircraft equipment failures, cabin problems and problems related to the environment of the aircraft; means of determination receiving data from the means of interpretation and determining at least one reference constraint associated with at least one parameter representative of a flight path, a reference constraint associated with a reference parameter comprising a new constraint, different from the initial constraint when the item of data effectively necessitates following a new path, different from the initial path, and a reference constraint comprising the initial constraint when the means of determination do not have access to any data relating to an event effectively necessitating following a new path; warning means generating a warning to an operator when the path actually flown does not comply with said reference constrai

Abstract: A method for aiding navigation for an aircraft between a descent start point and a computation end point, comprises the computation steps of: collecting a flight plan consisting of a succession of waypoints and of the associated vertical constraints; determining a corridor consisting of a floor trajectory and of a ceiling trajectory defining the minimum and maximum altitudes permitted to the aircraft; splitting the corridor into several cells defined between two waypoints furthest apart and between which the ceiling trajectory is distinct from the floor trajectory; determining for at least one cell a vertical trajectory complying with the altitude constraints and comprising the longest possible IDLE segment; and a step consisting in determining and displaying maneuvering points of the aircraft making it possible to follow the target vertical trajectory.

Abstract: A method is provided for managing the flight of an aircraft flying a trajectory calculated by a flight management system. The trajectory necessitates at least one transition between two different aerodynamic configurations of the aircraft. The method comprises: extraction of performance data of the aircraft from a database, at least one item of performance data being a function of an aerodynamic configuration, selection between a first determination step and a second determination step, a step of determination of a start point and of an end point of the transition between two aerodynamic configurations and engine speeds of an aircraft during a flight, the determination step being implemented by the flight management system and chosen from among the first and second determination steps, the determination step calculating the trajectory by numerical integration of the equations representative of the dynamics of the aircraft making use of the performance data of the aircraft.

Abstract: An aircraft piloting assistance method and system including determining at least one flyable slope with which the aircraft is assumed to be able to fly, based on a value of at least one flight parameter including the weight of the aircraft. The step for determining said slope or slopes with which the aircraft is able to fly, called flyable slopes is performed by a computer, and presenting the flyable slope to a decision-maker.

Abstract: The invention relates to a navigation aid method and device for an aircraft. The aircraft occupies a position PPOS outside its flight plan and seeks to rejoin the flight plan. The flight plan includes a succession of waypoints. A waypoint WPTi is called sequenced once the aircraft has passed by the waypoint WPTi at a lateral distance within the limits of the fixed sequencing conditions. The next unsequenced waypoint is called the active waypoint. The method includes the computation of at least one path to rejoin the flight plan from the current position PPOS, the computation of a potential active waypoint in the flight plan based on a rejoining path, the display of the potential active waypoint, if the pilot confirms the potential active waypoint, the sequencing of the waypoints situated upstream of the potential active waypoint, the said potential active waypoint becoming the new active waypoint.

Abstract: The invention relates to a method for aiding the setting of the barometric altitude of an aircraft equipped with a means (11, 12) for determining the altitude not using the barometric pressure, determining with the aid of the means (11, 12) for determining the altitude an altitude (Zv, Zi, Zr, Zh) and its relative precision (Pzv, Pzr), comparing the determined altitude (Zv, Zi, Zr, Zh) with a barometric altitude measured aboard the aircraft, generating an alert when the discrepancy between the determined altitude (Zv, Zi, Zr, Zh) and the measured barometric altitude exceeds a predefined value and proposing a barometric altitude setting value.

Abstract: The invention relates to a method of automatically managing the flight of an aircraft in turbulent air comprising notably the determination of the current speed (Vc), of an optimal turbulence speed (Vt), of a current thrust value (P). The data relating to a turbulence is acquired. An optimal turbulence speed is determined. Measuring a deviation (?) between the current speed (Vc) and the turbulence speed (Vt). Comparing the deviation (?) and a maximum deviation value (?max). Iterating k times of the previous three steps, to determine whether the deviation (?) is greater than the maximum deviation (?max) for the kth consecutive time, and the readjustment of the current thrust (P) so as to reduce the deviation (?) to a value less than that of the maximum deviation (?max) and to make the current speed (Vc) converge to the turbulence speed (Vt).

Abstract: The present invention relates to a method for estimating the touchdown point of the wheels of an aircraft on a landing runway and the distance to be traveled by the aircraft on the runway from the touchdown point to reach a controlled speed below which it can perform any maneuver on the ground. The method comprises an in-flight step of estimating a height and a speed of passage above the threshold of the runway. It also comprises an in-flight step of estimating the touchdown point of the wheels of the aircraft on the landing runway and the distance to be traveled to reach the controlled speed, on the basis of the estimation of the height and the speed of passage above the threshold of the runway. It also comprises a step while going on the runway of estimating the distance to be traveled from the real touchdown point to reach the controlled speed, taking account of the braking forces provided by the brakes, the airbrakes and the thrust reversers.

Abstract: The invention relates to a method for automatic detection of turbulence by a second aircraft, by information exchange between the second aircraft and at least a first aircraft. The first aircraft has means for transmitting information and the second aircraft has means for receiving the information transmitted by the first aircraft. The method includes the identification of information about turbulence liable to be encountered by the second aircraft, by analyzing the information received from the first aircraft. An alarm is activated on the basis of the turbulence information.

Abstract: This system ensures autonomous protection of an aircraft against deliberate crashes resulting from a malicious act of a person on board or a trajectory error. It comprises a prohibited zone anti-penetration (cons. anti-collision) rig OAPS (54) operating in the manner of a terrain anti-collision rig TAWS (51) but intervening at the level of the flight controls (12) so as to impose an avoidance trajectory on the aircraft (83) when the need therefor is felt. This prohibited zone anti-penetration (cons. anti-collision) rig OAPS (54) uses a database (60) holding information about the prohibited zones and a system for positioning (106, 306) of the aircraft (83). Supplemented with a terrain anti-collision rig TAWS (51) and a rig for protection of the limits of the flight domain FELPS (53), it makes it possible to produce a very complete flight protection system.