Abstract: A control system for an aircraft allowing a pilot of the aircraft to control aerodynamic means, the control system comprising a processing unit for generating control commands, the control commands being transmitted to control devices to modify a position of the aerodynamic means and to pilot the aircraft according to four control axes having a pitch control axis, a roll control axis, a yaw movement control axis and a lift control axis, the control system comprising a control member generating control setpoints, the control setpoints being transmitted to the processing unit generating the control commands under the dependency of the control setpoints, the control member being mechanically disconnected from the control devices.

Abstract: A method and a system for providing a rotorcraft with assistance in taking off from a slope. The rotorcraft includes at least one lift rotor provided with a plurality of blades, control devices for controlling the pitches of the blades, and landing gear provided with at least three ground contact members. The method comprises a step of measuring a piece of information relating to the forces to which each ground contact member is subjected during a landing phase for landing on the slope, a step of measuring at least one piece of information relating to the pitches of the blades during the landing phase, and a control step for controlling the pitches of the blades during the takeoff phase during which the rotorcraft takes off after the landing as a function of the measurements taken during the landing in order to enable a takeoff to be performed that is safe and simplified.

Abstract: An apparatus for sensing an elastic deformation of a hollow element, wherein the apparatus comprises at least one sensor that is arranged in a watertight capsule which is connected in a watertight manner to a connector device comprising at least one watertight electrical connector that is electrically connected to the at least one sensor, the at least one watertight electrical connector forming a first waterproof barrier of the connector device between an outside of the watertight capsule and the at least one sensor, and wherein the connector device comprises at least one further waterproof barrier that is formed between the first waterproof barrier and the at least one sensor.

Abstract: A control system for an aircraft allowing a pilot of the aircraft to control aerodynamic means, the control system comprising a processing unit for generating control commands, the control commands being transmitted to control devices to modify a position of the aerodynamic means and to pilot the aircraft according to four control axes having a pitch control axis, a roll control axis, a yaw movement control axis and a lift control axis, the control system comprising a control member generating control setpoints, the control setpoints being transmitted to the processing unit generating the control commands under the dependency of the control setpoints, the control member being mechanically disconnected from the control devices.

Abstract: A method and a system for providing a rotorcraft with assistance in taking off from a slope. The rotorcraft includes at least one lift rotor provided with a plurality of blades, control devices for controlling the pitches of the blades, and landing gear provided with at least three ground contact members. The method comprises a step of measuring a piece of information relating to the forces to which each ground contact member is subjected during a landing phase for landing on the slope, a step of measuring at least one piece of information relating to the pitches of the blades during the landing phase, and a control step for controlling the pitches of the blades during the takeoff phase during which the rotorcraft takes off after the landing as a function of the measurements taken during the landing in order to enable a takeoff to be performed that is safe and simplified.

Abstract: An apparatus for sensing an elastic deformation of a hollow element, wherein the apparatus comprises at least one sensor that is arranged in a watertight capsule which is connected in a watertight manner to a connector device comprising at least one watertight electrical connector that is electrically connected to the at least one sensor, the at least one watertight electrical connector forming a first waterproof barrier of the connector device between an outside of the watertight capsule and the at least one sensor, and wherein the connector device comprises at least one further waterproof barrier that is formed between the first waterproof barrier and the at least one sensor.

Abstract: A method of controlling a deflection angle of pitching stabilizer means for an aircraft. The method includes a preliminary stage for preparing at least one control relationship delivering a setpoint angle that is to be reached by the deflection angle as a function of at least one flight parameter of the aircraft and of an incidence parameter of the pitching stabilizer means. During an operational stage an operational stage (STP2), a “flight” value is determined for each of the flight parameters, a “setpoint” value is determined for the incidence parameter, a setpoint angle is determined by inputting the flight values and setpoint value into the control relationship, and at least one actuator is actuated in order to cause the deflection angle of the pitching stabilizer means to reach the setpoint angle.

Abstract: A method of controlling a deflection angle of pitching stabilizer means for an aircraft. The method includes a preliminary stage for preparing at least one control relationship delivering a setpoint angle that is to be reached by the deflection angle as a function of at least one flight parameter of the aircraft and of an incidence parameter of the pitching stabilizer means. During an operational stage an operational stage (STP2), a “flight” value is determined for each of the flight parameters, a “setpoint” value is determined for the incidence parameter, a setpoint angle is determined by inputting the flight values and setpoint value into the control relationship, and at least one actuator is actuated in order to cause the deflection angle of the pitching stabilizer means to reach the setpoint angle.

Abstract: A method of controlling and regulating a rotorcraft presenting a speed of advance that is high and stabilized, the rotorcraft including at least a main lift rotor (10), at least one variable pitch propulsion propeller (6), and at least one power plant for driving the main rotor(s) (10) and at least one propeller (6), said method consisting in using a first loop for regulating pitch or attitude, and a second loop for regulating speed by means of a control over the mean pitch of the propulsion propeller(s) (6), wherein the method further consists in controlling the deflection angle of a horizontal tailplane (30, 25, 35) by using a third loop for controlling and regulating said deflection angle of the horizontal tailplane (30, 25, 35) in order to minimize the total power consumed by the main rotor (10) and the propulsive propeller(s) (6), for a given speed and attitude.

Abstract: A method of controlling the yaw attitude of a hybrid helicopter including a fuselage and an additional lift surface provided with first and second half-wings extending from either side of the fuselage, each half-wing being provided with a respective first or second propeller. The hybrid helicopter has a thrust control suitable for modifying the first pitch of the first blades of the first propeller and the second pitch of the second blades of the second propeller by the same amount. The hybrid helicopter includes yaw control elements for generating an original order for modifying the yaw attitude of the hybrid helicopter by increasing the pitch of the blades of one propeller and decreasing the pitch of the blades of the other propeller, the original order is optimized as a function of the position of the thrust control to obtain an optimized yaw control order that is applied to the first and second blades.

Abstract: A method of controlling and regulating a rotorcraft presenting a speed of advance that is high and stabilized, the rotorcraft including at least a main lift rotor (10), at least one variable pitch propulsion propeller (6), and at least one power plant for driving the main rotor(s) (10) and at least one propeller (6), said method consisting in using a first loop for regulating pitch or attitude, and a second loop for regulating speed by means of a control over the mean pitch of the propulsion propeller(s) (6), wherein the method further consists in controlling the deflection angle of a horizontal tailplane (30, 25, 35) by using a third loop for controlling and regulating said deflection angle of the horizontal tailplane (30, 25, 35) in order to minimize the total power consumed by the main rotor (10) and the propulsive propeller(s) (6), for a given speed and attitude.

Abstract: A method of optimizing the operation of left and right propellers disposed on either side of the fuselage of a rotorcraft including a main rotor. Left and right aerodynamic surfaces include respective left and right flaps suitable for being deflected, yaw stabilization of the rotorcraft being achieved via first and second pitches respectively of the left and right propellers, and the deflection angles of the left and right flaps are adjusted solely during predetermined stages of flight in order to minimize a differential pitch of the left and right propellers so as to optimize the operation of the left and right propellers, the predetermined stages of flight including stages of flight at low speed performed at an indicated air speed (IAS) of the rotorcraft that is below a predetermined threshold, and stages of yaw-stabilized flight at high speed performed at an indicated air speed of the rotorcraft greater than the predetermined threshold.

Abstract: A method of controlling the yaw attitude of a hybrid helicopter including a fuselage and an additional lift surface provided with first and second half-wings extending from either side of the fuselage, each half-wing being provided with a respective first or second propeller. The hybrid helicopter has a thrust control suitable for modifying the first pitch of the first blades of the first propeller and the second pitch of the second blades of the second propeller by the same amount. The hybrid helicopter includes yaw control elements for generating an original order for modifying the yaw attitude of the hybrid helicopter by increasing the pitch of the blades of one propeller and decreasing the pitch of the blades of the other propeller, the original order is optimized as a function of the position of the thrust control to obtain an optimized yaw control order that is applied to the first and second blades.

Abstract: A method of optimizing the operation of left and right propellers disposed on either side of the fuselage of a rotorcraft including a main rotor. Left and right aerodynamic surfaces include respective left and right flaps suitable for being deflected, yaw stabilization of the rotorcraft being achieved via first and second pitches respectively of the left and right propellers, and the deflection angles of the left and right flaps are adjusted solely during predetermined stages of flight in order to minimize a differential pitch of the left and right propellers so as to optimize the operation of the left and right propellers, the predetermined stages of flight including stages of flight at low speed performed at an indicated air speed (IAS) of the rotorcraft that is below a predetermined threshold, and stages of yaw-stabilized flight at high speed performed at an indicated air speed of the rotorcraft greater than the predetermined threshold.