Abstract: A method for controlling an aircraft with a rotary wing provided with a power plant comprising a plurality of engines, the aircraft comprising a human-machine interface controlling a control member capable of acting on a longitudinal acceleration of the aircraft. During the economy operating mode during which one of the engines does not supply power, the method comprises measuring a forward speed of the aircraft, and adjusting an authority of the human-machine interface over the longitudinal acceleration with a flight control computer as a function of the forward speed.

Abstract: A method for checking a level of damage of at least one part of an aircraft. According to the disclosure, such a method comprises at least: a collection step for receiving data representative of measurements of at least one flight parameter, the data being generated during a mission of the aircraft by at least one embedded sensor; a projection step for projecting points onto a map in order to form an image point; an identification step for identifying, for each image point, an image zone in which the image point is located; and an analysis step for statistically analyzing the identified image zones and determining the level of damage of the at least one aircraft part.

Abstract: An aircraft and a method for controlling such an aircraft comprising two turboshaft engines, an electric machine, an electrical power source and a rotor rotated by one of the two turboshaft engines and/or by the electric machine. The aircraft comprises at least one controller configured to implement, at all times, a current operating mode of the electric machine and the electrical power source, selected from seven operating modes, allowing standard start-up or fast start-up respectively of a turboshaft engine in a switched-off state or in a standby state. The electric machine can also provide first or second levels of power assistance to a turboshaft engine in order to transmit engine torque to the gas generator of that turboshaft engine, apply mechanical resistance to a turboshaft engine or help ventilate a turboshaft engine in a switched-off state.

Abstract: An aircraft and a method for controlling such an aircraft comprising two turboshaft engines, an electric machine, an electrical power source and a rotor rotated by one of the two turboshaft engines and/or by the electric machine. The aircraft comprises at least one controller configured to implement, at all times, a current operating mode of the electric machine and the electrical power source, selected from seven operating modes, allowing standard start-up or fast start-up respectively of a turboshaft engine in a switched-off state or in a standby state. The electric machine can also provide first or second levels of power assistance to a turboshaft engine in order to transmit engine torque to the gas generator of that turboshaft engine, apply mechanical resistance to a turboshaft engine or help ventilate a turboshaft engine in a switched-off state.

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 controlling an aircraft with a rotary wing provided with a power plant comprising a plurality of engines, the aircraft comprising a human-machine interface controlling a control member capable of acting on a longitudinal acceleration of the aircraft. During the economy operating mode during which one of the engines does not supply power, the method comprises measuring a forward speed of the aircraft, and adjusting an authority of the human-machine interface over the longitudinal acceleration with a flight control computer as a function of the forward speed.

Abstract: A method for checking a level of damage of at least one part of an aircraft. According to the disclosure, such a method comprises at least: a collection step for receiving data representative of measurements of at least one flight parameter, the data being generated during a mission of the aircraft by at least one embedded sensor; a projection step for projecting points onto a map in order to form an image point; an identification step for identifying, for each image point, an image zone in which the image point is located; and an analysis step for statistically analyzing the identified image zones and determining the level of damage of the at least one aircraft part.

Abstract: A method and a system for stopping a gas turbine comprising a gas generator provided with rotary members and a combustion chamber. The gas turbine includes a fuel circuit controlled by calculation means in communication with a selector. The method includes a step of closing of the fuel circuit on order of the calculation means when the selector is positioned in a first position for causing the gas turbine to stop. If the gas turbine was not idling prior to the closure, or if it was idling, but for a length of time shorter than a threshold, then an electrical machine automatically rotates the rotary members for a limited duration.

Abstract: A method and a system for stopping a gas turbine comprising a gas generator provided with rotary members and a combustion chamber. The gas turbine includes a fuel circuit controlled by calculation means in communication with a selector. The method includes a step of closing of the fuel circuit on order of the calculation means when the selector is positioned in a first position for causing the gas turbine to stop. If the gas turbine was not idling prior to the closure, or if it was idling, but for a length of time shorter than a threshold, then an electrical machine automatically rotates the rotary members for a limited duration.

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.