Abstract: A flight control computer of an aircraft is likely to operate in a so-called incidence protection mode in which it is configured to compute the deflection orders of an elevator as a function of incidence angle values supplied by a set of incidence probes, so as to keep the incidence angle of the aircraft within a range of acceptable incidence angle values. The flight control computer is configured to, when only one incidence probe is operational: compute a first estimated incidence angle value of the aircraft, by a first estimator and a second estimated incidence angle value of the aircraft, by a second estimator unlike the first estimator; and keep the incidence protection mode activated as long as the incidence angle value supplied by the single operational incidence probe is consistent with at least one out of the first estimated incidence angle value and the second estimated incidence angle value.

Abstract: A flight control computer of an aircraft is likely to operate in a so-called incidence protection mode in which it is configured to compute the deflection orders of an elevator as a function of incidence angle values supplied by a set of incidence probes, so as to keep the incidence angle of the aircraft within a range of acceptable incidence angle values. The flight control computer is configured to, when only one incidence probe is operational: compute a first estimated incidence angle value of the aircraft, by a first estimator and a second estimated incidence angle value of the aircraft, by a second estimator unlike the first estimator; and keep the incidence protection mode activated as long as the incidence angle value supplied by the single operational incidence probe is consistent with at least one out of the first estimated incidence angle value and the second estimated incidence angle value.

Abstract: A device including a first data generating unit for determining at least one aerodynamic hinge moment of at least one control surface of the aircraft, a second data generating unit for determining a plurality of data and at least one external static pressure and a model of hinge moment coefficient, a computation unit for computing with the aid of these data at least one speed of the aircraft, namely a Mach number and/or a conventional speed, and a data transmission unit for providing this speed to a user system.

Abstract: A device including a first data generating unit for determining at least one aerodynamic hinge moment of at least one control surface of the aircraft, a second data generating unit for determining a plurality of data and at least one external static pressure and a model of hinge moment coefficient, a computation unit for computing with the aid of these data at least one speed of the aircraft, namely a Mach number and/or a conventional speed, and a data transmission unit for providing this speed to a user system.