Abstract: Method for controlling an unmanned aircraft piloted by a fully autonomous control system including a first decision module and a simplex piloting control module including a high-performance controller, a high-safety controller and a second decision module, the high-performance and high-safety controllers determining piloting commands for the robot-aircraft, according to which: —as long as a set of conditions is verified, implementation by the first decision module of a nominal piloting mode with delivery to the output of the automatic control system of the piloting commands delivered to the output of the simplex piloting control module; —otherwise, switching to an emergency piloting mode, an emergency piloting command is delivered to the output of the automatic control system for execution by the robot-aircraft, the first decision module preventing the delivery to the output of the automatic control system of the piloting commands delivered to the output of the simplex module.

Abstract: Methods and systems for assisting the piloting of an aircraft are provided. The system includes at least one avionics type system and at least one non-avionics type system. The method includes steps involving receiving avionics type data associated with a flying context of the aircraft; forwarding the avionics type data to a non-avionics type system or computer; determining, in the non-avionics computer, one or more adjustment recommendations for equipment based on the received flying context and/or on predetermined data; displaying one or more recommendations. Various developments are described, in particular the conditions for requesting and/or computing recommendations (e.g. ongoing adjustment of the avionics, similar previous configuration, etc.), the selection and the categorization of recommendations, the handling of adjustment data for the avionics, etc. Software aspects are described.

Abstract: Methods and systems for assisting the piloting of an aircraft are provided. The system includes at least one avionics type system and at least one non-avionics type system. The method includes steps involving receiving avionics type data associated with a flying context of the aircraft; forwarding the avionics type data to a non-avionics type system or computer; determining, in the non-avionics computer, one or more adjustment recommendations for equipment based on the received flying context and/or on predetermined data; displaying one or more recommendations. Various developments are described, in particular the conditions for requesting and/or computing recommendations (e.g. ongoing adjustment of the avionics, similar previous configuration, etc.), the selection and the categorization of recommendations, the handling of adjustment data for the avionics, etc. Software aspects are described.

Abstract: A method and device for displaying vertical constraints of an aircraft, an associated program produce and aircraft are disclosed. In one aspect, the vertical constrains are displayed on a display device of the aircraft, the display device being part of an aircraft piloting system, the method being implemented by an electronic device that is part of the aircraft piloting system. The method includes acquiring at least one vertical constraint of the aircraft, computing a representative slope value associated with the vertical constraint, and displaying a symbol depicting the vertical constraint at the representative slope value associated with the vertical constraint on a slope scale.

Abstract: This method makes it possible to generate a resulting setpoint trajectory of an aircraft, a guiding system controlling the trajectory of the aircraft relative to the resulting setpoint trajectory. The generating method is implemented by an electronic device and comprises selecting at least one mode from among several operating modes, acquiring a setpoint trajectory prepared by a flight management system, obtaining an alternative setpoint trajectory from an element from among a module for computing a trajectory and an external generating system, and generating the resulting setpoint trajectory, which includes one or several segments of the alternative setpoint trajectory for the period of time corresponding to the selection of another mode.

Abstract: This electronic device for aiding with the piloting of an aircraft includes: an acquisition module, configured to acquire a current value of the roll angle of the aircraft; a computing module configured to compute a roll angle limit corresponding to a beginning of stalling of the aircraft; and a display module, configured to display, on a screen, a first symbol indicating a current orientation of the aircraft. The computing module is configured to compute at least one roll margin, each roll margin depending on a corresponding roll angle limit and the current value of the roll angle, and the display module is configured, when the display condition is verified, to display, on the screen, at least one second symbol positioned relative to the first symbol, the deviation between each second symbol and the first symbol representing a respective roll margin.

Abstract: A method and device for controlling at least one actuator control system of an aircraft, an associated computer program product and aircraft are disclosed. In one aspect, the method includes determining a variation in thrust of the aircraft for controlling a variable relating to the aircraft relative to a set point, calculating a first control command signal to be sent to an engine control system in order to obtain the variation in thrust, and transmitting the first control command signal to the engine control system. The controlled variable can be an acceleration along a direction taken by a speed vector among the air speed vector and the ground speed vector and the set point can be an acceleration set point along the direction.

Abstract: A method for predicting a short-term flight path of an aircraft, a computer program product, an associated prediction device, a guidance method, and a guidance system of an aircraft are disclosed. In one aspect, the flight path of the aircraft is associated at each time moment with a vector including at least one component from among a position of the aircraft, attitudes of the aircraft and order 1 and 2 time derivatives of the position and attitudes. The short-term flight path is the flight path of the aircraft for a time period of up to 30 seconds from a computation time of the flight path. The method includes acquiring a control signal representative of a displacement of a primary control member of the aircraft and predicting, at a subsequent prediction time, at least one component of the short-term flight path of the aircraft.

Abstract: This method makes it possible to generate a resulting setpoint trajectory of an aircraft, a guiding system controlling the trajectory of the aircraft relative to the resulting setpoint trajectory. The generating method is implemented by an electronic device and comprises selecting at least one mode from among several operating modes, acquiring a setpoint trajectory prepared by a flight management system, obtaining an alternative setpoint trajectory from an element from among a module for computing a trajectory and an external generating system, and generating the resulting setpoint trajectory, which includes one or several segments of the alternative setpoint trajectory for the period of time corresponding to the selection of another mode.

Abstract: A method and device for generating at least one set point from a flight control set point, a motor control set point and an aircraft guidance set point, a related computer program product and an aircraft are disclosed. In one aspect, the method includes acquiring a mechanical property relative to at least one corresponding primary control member and computing at least one set point from among one or more primary set points and one or more secondary set points. The method also includes generating at least one of the computed set point(s) and switching, based on the mechanical property acquired for the corresponding primary control member, between a first mode in which one or more primary set points are generated and a second mode in which one or more secondary set points are generated.

Abstract: A method and device for displaying vertical constraints of an aircraft, an associated program produce and aircraft are disclosed. In one aspect, the vertical constrains are displayed on a display device of the aircraft, the display device being part of an aircraft piloting system, the method being implemented by an electronic device that is part of the aircraft piloting system.

Abstract: This electronic device for aiding with the piloting of an aircraft includes: an acquisition module, configured to acquire a current value of the roll angle of the aircraft; a computing module configured to compute a roll angle limit corresponding to a beginning of stalling of the aircraft; and a display module, configured to display, on a screen, a first symbol indicating a current orientation of the aircraft. The computing module is configured to compute at least one roll margin, each roll margin depending on a corresponding roll angle limit and the current value of the roll angle, and the display module is configured, when the display condition is verified, to display, on the screen, at least one second symbol positioned relative to the first symbol, the deviation between each second symbol and the first symbol representing a respective roll margin.

Abstract: A method and device for determining a control set point of an aircraft, an associated computer program and an aircraft are disclosed. In one aspect, the method includes calculating a performance scale in the form of slope values of the aircraft, the performance scale including a slope characteristic value, the slope characteristic value being associated with a corresponding performance characteristic value. The method also includes acquiring a guidance set point and displaying the acquired guidance set point, in the form of a slope value with respect to the performance scale. The method further includes determining a slope characteristic value associated with a guidance set point displayed in the form of a slope value, and calculating an aircraft control set point, the control set point being calculated relative to the performance characteristic value corresponding to the determined slope characteristic value.

Abstract: A method for securing a ground speed used for guiding landing of an aircraft by determining a ground speed of the aircraft and determining a landing guidance instruction based on the determined ground speed. Next, estimate the vertical speed of the aircraft and limit, during guidance along a glide path having a descent angle, the determined ground speed as a function of the estimated vertical speed. The guidance instruction is based on the limited ground speed. Further, measure the height of the aircraft and compare it with a threshold height. If the measured height is greater than the threshold height, limit the ground speed as a function of acceleration measurements. If the measured height is below the threshold height, limiting the ground speed as a function of the estimated vertical speed and as a function of acceleration measurements of the aircraft taken once threshold height has been crossed.

Abstract: A method and device for controlling at least one actuator control system of an aircraft, an associated computer program product and aircraft are disclosed. In one aspect, the method includes determining a variation in thrust of the aircraft for controlling a variable relating to the aircraft relative to a set point, calculating a first control command signal to be sent to an engine control system in order to obtain the variation in thrust, and transmitting the first control command signal to the engine control system. The controlled variable can be an acceleration along a direction taken by a speed vector among the air speed vector and the ground speed vector and the set point can be an acceleration set point along the direction.

Abstract: A method for predicting a short-term flight path of an aircraft, a computer program product, an associated prediction device, a guidance method, and a guidance system of an aircraft are disclosed. In one aspect, the flight path of the aircraft is associated at each time moment with a vector including at least one component from among a position of the aircraft, attitudes of the aircraft and order 1 and 2 time derivatives of the position and attitudes. The short-term flight path is the flight path of the aircraft for a time period of up to 30 seconds from a computation time of the flight path. The method includes acquiring a control signal representative of a displacement of a primary control member of the aircraft and predicting, at a subsequent prediction time, at least one component of the short-term flight path of the aircraft. The prediction step can be carried out at the computation time.

Abstract: A method and device for generating at least one set point from a flight control set point, a motor control set point and an aircraft guidance set point, a related computer program product and an aircraft are disclosed. In one aspect, the method includes acquiring a mechanical property relative to at least one corresponding primary control member and computing at least one set point from among one or more primary set points and one or more secondary set points. The method also includes generating at least one of the computed set point(s) and switching, based on the mechanical property acquired for the corresponding primary control member, between a first mode in which one or more primary set points are generated and a second mode in which one or more secondary set points are generated.

Abstract: A method and device for determining a control set point of an aircraft, an associated computer program and an aircraft are disclosed. In one aspect, the method includes calculating a performance scale in the form of slope values of the aircraft, the performance scale including a slope characteristic value, the slope characteristic value being associated with a corresponding performance characteristic value. The method also includes acquiring a guidance set point and displaying the acquired guidance set point, in the form of a slope value with respect to the performance scale. The method further includes determining a slope characteristic value associated with a guidance set point displayed in the form of a slope value, and calculating an aircraft control set point, the control set point being calculated relative to the performance characteristic value corresponding to the determined slope characteristic value.

Abstract: A method for securing a ground speed used for guiding landing of an aircraft by determining a ground speed of the aircraft and determining a landing guidance instruction based on the determined ground speed. Next, estimate the vertical speed of the aircraft and limit, during guidance along a glide path having a descent angle, the determined ground speed as a function of the estimated vertical speed. The guidance instruction is based on the limited ground speed. Further, measure the height of the aircraft and compare it with a threshold height. If the measured height is greater than the threshold height, limit the ground speed as a function of acceleration measurements. If the measured height is below the threshold height, limiting the ground speed as a function of the estimated vertical speed and as a function of acceleration measurements of the aircraft taken once threshold height has been crossed.

Abstract: Guidance for an aircraft correcting a trajectory deviation due to wind computes a roll command during trajectory alignment according to imposed alignment passing through a determined point, via a current angular divergence between a line through the point and aircraft and direction of alignment and of a current estimated ground speed of the aircraft with respect to a frame of reference. The current estimated ground speed is computed via a current air speed and stored wind speed. The stored wind speed is obtained via at least one wind speed computed via a first value of a first speed equal to the speed of the said aircraft with respect to a frame of reference originating from a satellite navigation system and a second value of a second speed equal to the air speed. The first and second value are simultaneously accounted earlier than or at the instant at the alignment phase.