Abstract: The estimation device comprises an estimation assembly for determining a corrected estimated incidence, with the aid of an estimated incidence which is computed on the basis of aerodynamic parameters and of inertial parameters related to the aircraft and of a measured incidence which is determined on the basis of measurements carried out on the aircraft by at least one incidence probe. This estimation device thus makes it possible to obtain estimations of the speed of the aircraft, of its incidence and of the total temperature, on the basis of aerodynamic and inertial parameters.

Abstract: A pilot assistance device includes information sources for determining automatically, in real time, a current vertical load factor of the aircraft, a computation unit for computing automatically, in real time, a flight director value using the current vertical load factor and a target vertical load factor representing a vertical load factor desired for the aircraft in the parabolic flight, the flight director value being computed in such a way as to be equal to a reference value when the current vertical load factor becomes equal to the target vertical load factor, and a display unit for presenting automatically, in real time, on a load factor scale, displayed on a screen of the cockpit of the aircraft, an indicator representative of the flight director value, computed by the computation unit, and an indicator indicating the reference value.

Abstract: A pilot assistance device includes information sources for determining automatically, in real time, a current vertical load factor of the aircraft, a computation unit for computing automatically, in real time, a flight director value using the current vertical load factor and a target vertical load factor representing a vertical load factor desired for the aircraft in the parabolic flight, the flight director value being computed in such a way as to be equal to a reference value when the current vertical load factor becomes equal to the target vertical load factor, and a display unit for presenting automatically, in real time, on a load factor scale, displayed on a screen of the cockpit of the aircraft, an indicator representative of the flight director value, computed by the computation unit, and an indicator indicating the reference value.

Abstract: The estimation device comprises an estimation assembly for determining a corrected estimated incidence, with the aid of an estimated incidence which is computed on the basis of aerodynamic parameters and of inertial parameters related to the aircraft and of a measured incidence which is determined on the basis of measurements carried out on the aircraft by at least one incidence probe. This estimation device thus makes it possible to obtain estimations of the speed of the aircraft, of its incidence and of the total temperature, on the basis of aerodynamic and inertial parameters.

Abstract: A method for estimating aircraft airspeed by a processor and an airspeed estimation device, which includes the calculation of a value for aircraft aerodynamic speed (Vcaero), by an aerodynamic calculator, based on aircraft aerodynamic parameters and the calculation of a value for current aircraft speed (Vc) by an anemobarometric unit. An estimated airspeed (Vcest) is determined by adding, by an adding unit, a corrective value, determined by an airspeed integrating unit, to the value for Vcaero. The corrective value is determined, by the airspeed integrating unit, according to a comparison between: a residual speed value (VR), determined by a residual speed determination unit, with the value VR determined by correcting the value for Vcaero to a value that converges toward the value for Vc, and a predetermined threshold value (?).

Abstract: According to the invention, an alert may be generated when a sudden inversion of the rudder occurs. To this end, the pilot having beforehand moved a commanding system in such a manner that the movement of the commanding system overcomes the position of the commanding system corresponding to the maximum rotation breakpoint in one of the rotating directions of the rudder. The alert is launched if, during a first time interval having a predetermined duration, the pilot moves the commanding system in such a manner that the movement of the commanding system overcomes the position of the commanding system corresponding to the maximum rotation breakpoint in the other rotating direction of the rudder, thereby indicating a sudden rudder inversion and a potential unsafe condition to be corrected by the pilot.

Abstract: Method and device for automatically estimating an airspeed of an aircraft The device (1) includes means (6) for determining an estimated airspeed with the aid of an aerodynamic airspeed which is calculated from current values of aircraft parameters and a speed which is generated by an air data computer (8).

Abstract: According to the invention, the pilot having beforehand moved a commanding system in such a manner that the movement of said system (6) overcomes the position of said system corresponding to the maximum rotation breakpoint in one of the rotating directions of the rudder (5), an alert is launched if, during a first time interval having a predetermined duration, said pilot moves said commanding system in such a manner that the movement of said system. (6) overcomes the position of said system corresponding to the maximum rotation breakpoint in the other rotating direction of said rudder (5).

Abstract: The piloting system (1) for generating orders for piloting the aircraft according to at least one piloting axis, for example the pitch axis, the roll axis, the yaw axis or the engine thrust control axis, comprises at least two piloting means (2, 3), each of which is capable of calculating the derivative with respect to time of the function which represents the corresponding piloting law and which takes into account the current values of parameters of the aircraft, first means (4) for intercomparing the derivatives calculated by the piloting means (2, 3) and for selecting a derivative; and second means (10) for integrating a selected derivative in such a way as to obtain said piloting order according to said piloting axis.