Abstract: A method for determining an estimated mass of an aircraft is provided. This method includes determining a first mass of the aircraft, from characteristics of the aircraft determined before or after takeoff of the aircraft, determining, during the flight of the aircraft, a second mass of the aircraft, from a lift equation of the aircraft expressing the mass of the aircraft as a function of information representative of the load factor of the aircraft, of a lift coefficient of the aircraft, of speed information of the aircraft and of a static pressure of a mass of air passed through by the aircraft, determined from measurements by sensors of the aircraft during the flight of the aircraft, evaluating the estimated mass at said determination moment, as a function of said first and second masses.

Abstract: A method for determining a state of credibility of measurements made by sensors of an aircraft is provided. This method includes determining a speed of the aircraft, from static and total pressure measurements, determining a coefficient of lift of the aircraft from an incidence measurement and from said speed, determining a weight of the aircraft, determining if an equation of lift of the aircraft is satisfied, activating a state of optimal credibility, wherein the measurements made by said sensors are considered to be reliable if the said equation of lift is satisfied, activating a state of non-optimal credibility, wherein the measurements of at least one sensor are considered to be unreliable if the said equation of lift is not satisfied.

Abstract: A method for determining a state of credibility of measurements of an angle-of-attack sensor of an aircraft is provided. This method includes at least one coherence test between angle-of-attack measurements from said angle-of-attack sensor, and the measurements of a flight characteristic of the aircraft, distinct from the angle-of-attack. The coherence test includes determining an angle-of-attack value from said angle-of-attack sensor, determining said flight characteristic of the aircraft, determining a value of at least one indicator of the coherence of the angle-of-attack value with the value of said flight characteristic, and activating a low state of credibility, in which the measurements of said angle-of-attack sensor are deemed unreliable, or an intermediate state of credibility, in which the measurements from said angle-of-attack sensor are deemed coherent with said flight characteristic, based on the value of said coherence indicator.

Abstract: A device is provided for assisting in the piloting of a vehicle, in particular an aircraft. The device includes a surface displaying images and a display management unit for images designed to be displayed on the display surface superimposed on a view of the outside landscape. The management unit is capable of commanding the display of piloting information images on the display surface. The management unit is capable of commanding the display, for at least one of the piloting information images, of an animation intended to attract a user's attention to that piloting information image, the animation comprising the display of an alert image and the shrinkage of the alert image.

Abstract: A device for displaying flight characteristics of an aircraft is provided. The device includes a display for the selective display of flight characteristics of an aircraft, as a function of a state of credibility assigned to measurements from static pressure, total pressure and angle-of-attack sensors, configured for selectively displaying a primary set of flight characteristics comprising at least one flight characteristic coming from a measurement from one of said sensors, when the measurements from said sensors are deemed reliable, and a secondary set of flight characteristics, distinct from said primary set, comprising at least one secondary flight characteristic designed to replace a counterpart flight characteristic from the primary set, when the measurements from at least one sensor are deemed unreliable, said secondary flight characteristic being independent of any measurement by the or each sensor deemed unreliable done when the measurements from that sensor are deemed unreliable.

Abstract: A method for determining an estimated mass of an aircraft is provided. This method includes determining a first mass of the aircraft, from characteristics of the aircraft determined before or after takeoff of the aircraft, determining, during the flight of the aircraft, a second mass of the aircraft, from a lift equation of the aircraft expressing the mass of the aircraft as a function of information representative of the load factor of the aircraft, of a lift coefficient of the aircraft, of speed information of the aircraft and of a static pressure of a mass of air passed through by the aircraft, determined from measurements by sensors of the aircraft during the flight of the aircraft, evaluating the estimated mass at said determination moment, as a function of said first and second masses.

Abstract: A method for determining a state of credibility of measurements of an incidence sensor of an aircraft is provided. This method includes at least one coherence test between incidence measurements from said incidence sensor, and the measurements of a flight characteristic of the aircraft, distinct from the incidence. The coherence test includes determining an incidence value from said incidence sensor, determining said flight characteristic of the aircraft, determining a value of at least one indicator of the coherence of the incidence value with the value of said flight characteristic, and activating a low state of credibility, in which the measurements of said incidence sensor are deemed unreliable, or an intermediate state of credibility, in which the measurements from said incidence sensor are deemed coherent with said flight characteristic, based on the value of said coherence indicator.

Abstract: A method for determining a state of credibility of measurements made by sensors of an aircraft is provided. This method includes determining a speed of the aircraft, from static and total pressure measurements, determining a coefficient of lift of the aircraft from an incidence measurement and from said speed, determining a weight of the aircraft, determining if an equation of lift of the aircraft is satisfied, activating a state of optimal credibility, wherein the measurements made by said sensors are considered to be reliable if the said equation of lift is satisfied, activating a state of non-optimal credibility, wherein the measurements of at least one sensor are considered to be unreliable if the said equation of lift is not satisfied.

Abstract: A device for displaying flight characteristics of an aircraft is provided. The device includes a display for the selective display of flight characteristics of an aircraft, as a function of a state of credibility assigned to measurements from static pressure, total pressure and incidence sensors, configured for selectively displaying a primary set of flight characteristics comprising at least one flight characteristic coming from a measurement from one of said sensors, when the measurements from said sensors are deemed reliable, and a secondary set of flight characteristics, distinct from said primary set, comprising at least one secondary flight characteristic designed to replace a counterpart flight characteristic from the primary set, when the measurements from at least one sensor are deemed unreliable, said secondary flight characteristic being independent of any measurement by the or each sensor deemed unreliable done when the measurements from that sensor are deemed unreliable.

Abstract: A device is provided for assisting in the piloting of a vehicle, in particular an aircraft. The device includes a surface displaying images and a display management unit for images designed to be displayed on the display surface superimposed on a view of the outside landscape. The management unit is capable of commanding the display of piloting information images on the display surface. The management unit is capable of commanding the display, for at least one of the piloting information images, of an animation intended to attract a user's attention to that piloting information image, the animation comprising the display of an alert image and the shrinkage of the alert image.

Abstract: The method for managing an energy variation of an aircraft provided with at least one propulsion system, capable of generating a thrust force on said aircraft comprised in a thrust range, is characterized in that said energy variation is expressed by a size representative of said energy variation and homogenous to a gradient of the aircraft, and in that it includes steps for determining the current energy variation of said aircraft, ordering an energy variation of the aircraft, determining, as a function of said ordered energy variation, a necessary thrust force that must be generated by said propulsion system for the energy variation of the aircraft to be able to tend towards said ordered energy variation, and developing and applying a control order to said propulsion system so that it delivers said necessary thrust force.

Abstract: The method for managing an energy variation of an aircraft provided with at least one propulsion system, capable of generating a thrust force on said aircraft comprised in a thrust range, is characterized in that said energy variation is expressed by a size representative of said energy variation and homogenous to a gradient of the aircraft, and in that it includes steps for determining the current energy variation of said aircraft, ordering an energy variation of the aircraft, determining, as a function of said ordered energy variation, a necessary thrust force that must be generated by said propulsion system for the energy variation of the aircraft to be able to tend towards said ordered energy variation, and developing and applying a control order to said propulsion system so that it delivers said necessary thrust force.