Abstract: The present disclosure relates to a system and a method for assisting the piloting of an aircraft, said method comprising, during a flight phase of said aircraft, at least two steps of measuring at least two current values of at least two respective operating parameters of said aircraft. The method comprises, for each of said at least two operating parameters, the following steps: generating an item of digital data representative of a current value of this operating parameter; identifying a current range within which an index lies, each range from said at least two ranges of indices being associated with a specific display configuration of said item of digital data; and displaying said item of digital data on at least one page of symbologies according to said specific display configuration corresponding to said current range.

Abstract: A device for monitoring an available thrust margin of an anti-torque member of a rotorcraft as a function of flight conditions, said rotorcraft comprising a power plant driving at least one main rotor participating at least in the lift of said rotorcraft, said anti-torque member participating in the control of the yaw movements of said rotorcraft.

Abstract: A method of facilitating the piloting of a hybrid rotorcraft that comprises a lift rotor and at least one propulsion rotor together with at least one engine operating in compliance with at least one rating. For at least one rating, onboard calculator determines a first power margin of the power plant that is available for the lift rotor and at least one second power margin that is available for said at least one propulsion rotor. A single indicator displays a line together with a first index pointing to said line to illustrate a current operating point of the lift rotor, and a second index pointing to said line to illustrate a current operating point of said at least one propulsion rotor. For each monitored rating, a first symbol is spaced apart from the first index by a first distance illustrating the first power margin. A second symbol is spaced apart from the second index by a second distance illustrating the second power margin.

Abstract: A method for stopping an engine of a rotorcraft in overspeed, the rotorcraft comprising at least one engine, the engine comprising a gas generator and a power assembly, the power assembly comprising at least one power turbine rotated by gases originating from the gas generator, the power assembly comprising at least one power shaft rotationally secured to the power turbine, the power assembly rotating about a longitudinal axis at a speed referred to as the “speed of rotation”. The method comprises steps consisting in measuring a current value of the speed of rotation, determining a time derivative of the current value of the speed of rotation, referred to as the “current derivative ( d ? ? N ? ? 2 ? ? i d ? t ) ” , and automatically stopping the engine when the current derivative ( d ? ? N ? ? 2 ? ? i d ? t ) changes sign.

Abstract: A method for stopping an engine of a rotorcraft in overspeed, the rotorcraft comprising at least one engine, the engine comprising a gas generator and a power assembly, the power assembly comprising at least one power turbine rotated by gases originating from the gas generator, the power assembly comprising at least one power shaft rotationally secured to the power turbine, the power assembly rotating about a longitudinal axis at a speed referred to as the “speed of rotation”. The method comprises steps consisting in measuring a current value of the speed of rotation, determining a time derivative of the current value of the speed of rotation, referred to as the “current derivative ( d ? ? N ? ? 2 ? ? i d ? t ) ” , and automatically stopping the engine when the current derivative ( d ? ? N ? ? 2 ? ? i d ? t ) changes sign.

Abstract: A device for monitoring an available thrust margin of an anti-torque member of a rotorcraft as a function of flight conditions, said rotorcraft comprising a power plant driving at least one main rotor participating at least in the lift of said rotorcraft, said anti-torque member participating in the control of the yaw movements of said rotorcraft.

Abstract: A method of driving a main rotor of a rotorcraft in rotation while implementing an in-flight simulation mode that simulates failure of one of the engines of the rotorcraft. In simulation mode, and when a current speed of rotation (NR) of the main rotor is detected as being lower than a predetermined threshold speed of rotation (S), the simulation mode is kept active and a regulation command is generated in order to perform a controlled operation (A) of gradually increasing the power delivered by the engines by authorizing the limit imposed by a setpoint (OEI/2) for regulating operation of the engine in simulation mode to be exceeded. Said gradually increasing power is interrupted by the pilot staying under training and operating a collective pitch manoeuver of the blade of the main rotor providing a rotation of main rotor at the predetermined threshold speed in rotation.

Abstract: A method of facilitating the piloting of a hybrid rotorcraft that comprises a lift rotor and at least one propulsion rotor together with at least one engine operating in compliance with at least one rating. For at least one rating, onboard calculator determines a first power margin of the power plant that is available for the lift rotor and at least one second power margin that is available for said at least one propulsion rotor. A single indicator displays a line together with a first index pointing to said line to illustrate a current operating point of the lift rotor, and a second index pointing to said line to illustrate a current operating point of said at least one propulsion rotor. For each monitored rating, a first symbol is spaced apart from the first index by a first distance illustrating the first power margin. A second symbol is spaced apart from the second index by a second distance illustrating the second power margin.

Abstract: A method and a device for controlling a coupling mechanism arranged between an engine and a main mechanical power transmission gearbox MGB of a rotary wing aircraft. First determination means enable a first measurement to be taken giving the speed of rotation of said engine, which speed, on being compared with a setpoint speed for said engine, makes it possible to determine a “ready to engage” state for said coupling mechanism. Third determination means serve to determine a maximum torque that can be accepted by said MGB. While engaging the coupling mechanism, a control system for controlling said engine regulates said speed of rotation of said engine on said setpoint speed, while ensuring that the torque delivered by said engine is less than or equal to said maximum acceptable torque.

Abstract: A method and a device for controlling a coupling mechanism arranged between an engine and a main mechanical power transmission gearbox MGB of a rotary wing aircraft. First determination means enable a first measurement to be taken giving the speed of rotation of said engine, which speed, on being compared with a setpoint speed for said engine, makes it possible to determine a “ready to engage” state for said coupling mechanism. Third determination means serve to determine a maximum torque that can be accepted by said MGB. While engaging the coupling mechanism, a control system for controlling said engine regulates said speed of rotation of said engine on said setpoint speed, while ensuring that the torque delivered by said engine is less than or equal to said maximum acceptable torque.

Abstract: A method of driving a main rotor of a rotorcraft in rotation while implementing an in-flight simulation mode that simulates failure of one of the engines of the rotorcraft. In simulation mode, and when a current speed of rotation (NR) of the main rotor is detected as being lower than a predetermined threshold speed of rotation (S), the simulation mode is kept active and a regulation command is generated in order to perform a controlled operation (A) of gradually increasing the power delivered by the engines by authorizing the limit imposed by a setpoint (OEI/2) for regulating operation of the engine in simulation mode to be exceeded. Said gradually increasing power is interrupted by the pilot staying under training and operating a collective pitch maneuver of the blade of the main rotor providing a rotation of main rotor at the predetermined threshold speed in rotation.

Abstract: A method of stopping an overspeeding engine (4) of a rotorcraft (1). A protection device stops the overspeeding engine (4) on condition of a comparison between a mechanical power requirement (19) of the rotorcraft (1) and a predefined power threshold (22). Stopping of the overspeeding engine (4) is authorized by the protection device (8) on condition that said mechanical power requirement (19) is identified as being less than or equal to the predefined power threshold (22). The mechanical power requirement (19) of the rotorcraft (1) is calculated on the basis of at least one current or anticipated value for the opposing torque (15) of a main rotor (5) of the rotorcraft.

Abstract: A method of stopping an overspeeding engine (4) of a rotorcraft (1). A protection device stops the overspeeding engine (4) on condition of a comparison between a mechanical power requirement (19) of the rotorcraft (1) and a predefined power threshold (22). Stopping of the overspeeding engine (4) is authorized by the protection device (8) on condition that said mechanical power requirement (19) is identified as being less than or equal to the predefined power threshold (22). The mechanical power requirement (19) of the rotorcraft (1) is calculated on the basis of at least one current or anticipated value for the opposing torque (15) of a main rotor (5) of the rotorcraft.

Abstract: A method of driving a main rotor of a rotorcraft in rotation while implementing an in-flight simulation mode that simulates failure of one of the engines of the rotorcraft. In simulation mode, and when a current speed of rotation (NR) of the main rotor is detected as being lower than a predetermined threshold speed of rotation (S), the simulation mode is kept active and a regulation command is generated in order to perform a controlled operation (A) of gradually increasing the power delivered by the engines by authorizing the limit imposed by a setpoint (OEI/2) for regulating operation of the engine in simulation mode to be exceeded. Said gradually increasing power is interrupted by the pilot staying under training and operating a collective pitch manoeuver of the blade of the main rotor providing a rotation of main rotor at the predetermined threshold speed in rotation.