Abstract: The present invention relates to a control method in case of engine failure of a hybrid helicopter having a power plant connected to at least one lift rotor and to at least one propeller, said lift rotor having a plurality of first blades and said at least one propeller having a plurality of second blades. The method comprises the following steps: (i) measuring a forward speed of the hybrid helicopter, (ii) on condition that said forward speed is greater than a first speed threshold and that each engine has failed, automatically implementing a first emergency piloting mode comprising a step for automatic reduction by an automatic piloting system of a pitch of said second blades toward an objective pitch making said at least one propeller produce a motive power which is transmitted to the lift rotor.

Abstract: A rotorcraft including a first power plant, at least one main rotor participating at least in providing lift for the rotorcraft in the air, and at least one tail rotor carried by a tail boom, the first power plant including at least one engine. In accordance with the invention, the rotorcraft includes: at least one pusher or puller propeller independent from the at least one main rotor, the at least one pusher or puller propeller participating at least in providing propulsion or traction for the rotorcraft; a second power plant including at least one electric motor; and at least one control member configured to generate a control setpoint or instruction for controlling the at least one electric motor.

Abstract: A hybrid type rotorcraft having a main rotor, at least two propulsion elements each mounted on respective half-wings arranged symmetrically on either side of an anteroposterior midplane XOZ, a horizontal stabilizer arranged in a rear zone of the rotorcraft on either side of the anteroposterior midplane XOZ, and two fins arranged respectively on either side of the anteroposterior midplane XOZ, each of the two fins comprising a respective left/right bottom fin airfoil arranged below the horizontal stabilizer and a respective left/right top fin airfoil arranged above the horizontal stabilizer.

Abstract: A method of improving a blade and also an improved blade and a advancement propeller including the improved blade. The radius of the initial leading edge circle of each airfoil of the blade is increased, and its leading edge is moved away from a pressure side half-airfoil towards a suction side half-airfoil, thereby modifying the airfoil of each cross-section of the blade and modifying the camber of each airfoil. Consequently, the absolute value of the negative stall angle of attack of the blade is increased, thus making it possible to increase the aerodynamic performance of the blade under a negative angle of attack compared with a blade that is not modified, and without significantly degrading its aerodynamic performance under a positive angle of attack.

Abstract: A method of determining an initial leading edge circle for airfoils of a blade and of improving a blade, and also an improved blade and a advancement propeller including the improved blade. The radius of the initial leading edge circle of each airfoil of the blade is determined and then increased, and its leading edge is moved away from a pressure side half-airfoil towards a suction side half-airfoil, thereby modifying the airfoil of each cross-section of the blade and modifying the camber of each airfoil. Consequently, the absolute value of the negative stall angle of attack of the blade is increased, thus making it possible to increase the aerodynamic performance of the blade under a negative angle of attack compared with a blade that is not modified, and without significantly degrading its aerodynamic performance under a positive angle of attack.

Abstract: A hybrid type rotorcraft having a main rotor, at least two propulsion elements each mounted on respective half-wings arranged symmetrically on either side of an anteroposterior midplane XOZ, a horizontal stabilizer arranged in a rear zone of the rotorcraft on either side of the anteroposterior midplane XOZ, and two fins arranged respectively on either side of the anteroposterior midplane XOZ, each of the two fins comprising a respective left/right bottom fin airfoil arranged below the horizontal stabilizer and a respective left/right top fin airfoil arranged above the horizontal stabilizer.

Abstract: An autopilot device and method for automatically piloting a rotary wing aircraft, having at least one propulsion propeller, the rotary wing including at least one rotor with blades, the device including a processor co-operating with at least one collective control system for controlling the collective pitch of the blades. The device includes engagement means connected to the processor for engaging an assisted mode of piloting for maintaining an angle of attack, the processor automatically controlling the collective pitch of the blades when the assisted mode of piloting for maintaining an angle of attack is engaged by controlling the collective control system to maintain an aerodynamic angle of attack (?) of the aircraft at a reference angle of attack (?*).

Abstract: An autopilot device (10) and method for automatically piloting a rotary wing aircraft (1), having at least one propulsion propeller (2), said rotary wing comprising at least one rotor (3) with a plurality of blades (3?), said device comprising a processor unit (15) co-operating with at least one collective control system (7) for controlling the collective pitch of said blades (3?). The device includes engagement means (20) connected to the processor unit (15) for engaging an assisted mode of piloting for maintaining an angle of attack, said processor unit (15) automatically controlling the collective pitch of the blades (3?) when the assisted mode of piloting for maintaining an angle of attack is engaged by controlling said collective control system to maintain an aerodynamic angle of attack (?) of the aircraft at a reference angle of attack (?*).

Abstract: An autopilot device and method for automatically piloting a rotary wing aircraft, having at least one propulsion propeller, the rotary wing including at least one rotor with blades, the device including a processor co-operating with at least one collective control system for controlling the collective pitch of the blades. The device includes engagement means connected to the processor for engaging an assisted mode of piloting for maintaining an angle of attack, the processor automatically controlling the collective pitch of the blades when the assisted mode of piloting for maintaining an angle of attack is engaged by controlling the collective control system to maintain an aerodynamic angle of attack (?) of the aircraft at a reference angle of attack (?*).

Abstract: A rotorcraft having at least one stabilizer device of the tail plane and/or of the tail fin type. At least one stabilizer device is a variable wing area stabilizer device comprising an airfoil member provided with a stationary airfoil surface and a movable airfoil surface. A control system is connected to a mover system for moving the movable airfoil surface in translation between a refracted position for occupying when the rotorcraft has a forward speed less than a first speed threshold, and an extended position for occupying when the rotorcraft has a forward air speed greater than a second speed threshold greater than the first speed threshold.

Abstract: A rotorcraft having at least one stabilizer device of the tail plane and/or of the tail fin type. At least one stabilizer device is a variable wing area stabilizer device comprising an airfoil member provided with a stationary airfoil surface and a movable airfoil surface. A control system is connected to a mover system for moving the movable airfoil surface in translation between a refracted position for occupying when the rotorcraft has a forward speed less than a first speed threshold, and an extended position for occupying when the rotorcraft has a forward air speed greater than a second speed threshold greater than the first speed threshold.

Abstract: A hybrid helicopter includes a rotary wing, two half-wings with respective propellers, and an engine installation continuously driving the rotary wing and the propellers by meshing with a mechanical interconnection system. A piloting assistance device for the hybrid helicopter is configured to determine maximum mean pitch (?max) applicable to the propellers without exceeding the power available for the propellers. The piloting assistance device is configured to determine the maximum mean pitch (?max) as a function of the current mean pitch of the blades of the propellers as measured in real time, a maximum power that can be delivered by the engine installation, a current power being delivered by the engine installation, and a relationship determining a power gradient (GRD) as a function of pitch for the propellers.

Abstract: A piloting assistance device for a hybrid helicopter is provided with a rotary wing, two half-wings (8?, 8?) provided respectively with first and second propellers (6?, 6?), and an engine installation continuously driving the rotary wing (100) and the propellers by meshing with a mechanical interconnection system. Furthermore, the device is provided with computer element (40) for determining maximum mean pitch (max) applicable to the first and second propellers without exceeding the power available for the propellers, the computer element determining the maximum mean pitch (max) as a function of the current mean pitch of the blades of the first and second propellers as measured in real time, of a maximum power that can be delivered by the engine installation, of a current power being delivered by the engine installation, and of a relationship determining a power gradient (GRD) as a function of pitch for the first and second propellers.

Abstract: A method of controlling a high speed rotary wing aircraft (1) comprising: a fuselage (2); at least one main rotor (3); at least one variable pitch propulsive propeller (4); at least two half-wings (11, 11?) positioned on either side of said fuselage (2); at least one horizontal stabilizer (20) provided with a movable surface (21, 21?); and at least one power plant driving said main rotor (3) and each propulsive propeller (4) in rotation. Said method serves to adjust the lift of said half-wings (11, 11?) and the lift of the horizontal stabilizer (20) so that the collective pitch of said blades (31) of said main rotor (3) is equal to a setpoint collective pitch, so that the longitudinal cyclic pitch of said blades (31) of said main rotor (3) is equal to a setpoint longitudinal cyclic pitch, and so that the lateral cyclic pitch of said blades (31) of said main rotor (3) is equal to a setpoint lateral cyclic pitch during a stabilized stage of flight.

Abstract: A method of controlling a high-speed rotary wing aircraft (1) comprising a fuselage (2), at least one main rotor (3), at least one variable-pitch propulsive propeller (4), at least two half-wings (11, 11?) positioned on either side of said fuselage (2), at least one horizontal stabilizer (20) provided with a movable surface (21, 21?), and at least one power plant driving said main rotor (3) and said propulsive propeller (4) in rotation. Said method serves to adjust the lift of said half-wings (11, 11?) and the lift of the horizontal stabilizer (20) so that said lift of said half-wings (11, 11?) represents a predetermined percentage of the total lift of said aircraft (1) and so that the power consumed by said main rotor (3) is equal to a setpoint power during a stage of stabilized flight.

Abstract: A hybrid helicopter includes a rotary wing, two half-wings with respective propellers, and an engine installation continuously driving the rotary wing and the propellers by meshing with a mechanical interconnection system. A piloting assistance device for the hybrid helicopter is configured to determine maximum mean pitch (?max) applicable to the propellers without exceeding the power available for the propellers. The piloting assistance device is configured to determine the maximum mean pitch (?max) as a function of the current mean pitch of the blades of the propellers as measured in real time, a maximum power that can be delivered by the engine installation, a current power being delivered by the engine installation, and a relationship determining a power gradient (GRD) as a function of pitch for the propellers.

Abstract: An aircraft (1) comprising a fuselage (2), a rotary wing (10) having two contrarotating main rotors (12) arranged in tandem above the fuselage (2), at least one propulsion member (20), and a power plant (30). Each propulsion member (20) is carried by a rear portion (3) of the fuselage. The aircraft (1) includes an interconnection system (40) providing a permanent connection between the power plant (30) and the rotary wing (10), except in the event of a failure or during training, the aircraft (1) having differential control means (50) for controlling the cyclic pitch of the blades of the main rotors (12) to control the aircraft (1) in yaw, and inhibition means (60) for inhibiting each propulsion member (20).

Abstract: A piloting assistance device (5) comprising a calculation unit (10) and a display unit (20). The calculation unit (10) executes stored instructions to determine at least one thrust margin for a propeller between a current thrust being exerted by said propeller and a threshold thrust corresponding to a negative power limit (Pmin), and to determine a main minimum total ground slope that can be followed by the aircraft in descent as a function of said thrust margin. Finally, the calculation unit presents a main symbol (25) on a display unit (20), the main symbol (25) representing the minimum total ground slope that can be followed by the aircraft (1) in descent, the main symbol (25) appearing superimposed on a representation (21) of the surroundings that exist in front of the aircraft (1).

Abstract: A device (10) for assisted piloting of an aircraft having a rotary wing with a plurality of second blades (3?) and a propulsion unit with a plurality of first blades (2?). The device includes control means (30, 40) for delivering a movement order (O) for moving in a direction, said device (10) having a processor unit (20) for transforming said order (O) into an acceleration setpoint (C) along said direction, and then for transforming said acceleration setpoint (C) into at least one required longitudinal attitude setpoint (?*) that is transmitted to a first automatic system (26) for maintaining longitudinal attitude by controlling a longitudinal cyclic pitch of the second blades (3?), and into a first required load factor setpoint (Nx*) in a longitudinal direction that is transmitted to a second automatic system (25) for maintaining load factor by controlling the collective pitch of the first blades.

Abstract: A method of controlling a high-speed rotary wing aircraft (1) comprising a fuselage (2), at least one main rotor (3), at least one variable-pitch propulsive propeller (4), at least two half-wings (11, 11?) positioned on either side of said fuselage (2), at least one horizontal stabilizer (20) provided with a movable surface (21, 21?), and at least one power plant driving said main rotor (3) and said propulsive propeller (4) in rotation. Said method serves to adjust the lift of said half-wings (11, 11?) and the lift of the horizontal stabilizer (20) so that said lift of said half-wings (11, 11?) represents a predetermined percentage of the total lift of said aircraft (1) and so that the power consumed by said main rotor (3) is equal to a setpoint power during a stage of stabilized flight.