The invention relates to a force application device for an aircraft control stick comprising: —a casing (24), —an electromagnet (22) mounted on the casing (24), —an actuator (30) mounted on the shaft (13), the actuator (30) being mobile in translation in relation to the shaft (13) along the axis (A), the actuator (30) comprising a magnetic material, and —a coupling device comprising an input gear (40) that is mounted so as to be stationary in relation to the casing (24) and an output gear (50) connected to the actuator (30) by means of an attachment part (60), the attachment part (60) being configured so as to allow a limited angular displacement between the output gear (50) and the shaft (13) around the axis (A) and to allow the actuator (30) of the output gear (50) to translate along the axis (A).

The invention relates to a force application device for an aircraft control stick comprising: —a casing (24), —an electromagnet (22) mounted on the casing (24), —an actuator (30) mounted on the shaft (13), the actuator (30) being mobile in translation in relation to the shaft (13) along the axis (A), the actuator (30) comprising a magnetic material, and —a coupling device comprising an input gear (40) that is mounted so as to be stationary in relation to the casing (24) and an output gear (50) connected to the actuator (30) by means of an attachment part (60), the attachment part (60) being configured so as to allow a limited angular displacement between the output gear (50) and the shaft (13) around the axis (A) and to allow the actuator (30) of the output gear (50) to translate along the axis (A).

An rotorcraft including a pilot control, a pilot control position sensor connected to the pilot control and operable to generate a position signal indicating a position of the pilot control, a flight control computer (FCC) in signal communication with the pilot control position sensor and operable to provide a tactile cue in the pilot control in response to the position signal indicating the position of the pilot control exceeds a threshold associated with an operating limit, and further operable to determine a tactile cueing value for the tactile cue according to a relationship between the position of the pilot control and the threshold, and generate a cue control signal according to the tactile cueing value, and a tactile cue element connected to the pilot control and in signal communication with the FCC and operable to control action of the pilot control in response to the cue control signal.

An rotorcraft including a pilot control, a pilot control position sensor connected to the pilot control and operable to generate a position signal indicating a position of the pilot control, a flight control computer (FCC) in signal communication with the pilot control position sensor and operable to provide a tactile cue in the pilot control in response to the position signal indicating the position of the pilot control exceeds a threshold associated with an operating limit, and further operable to determine a tactile cueing value for the tactile cue according to a relationship between the position of the pilot control and the threshold, and generate a cue control signal according to the tactile cueing value, and a tactile cue element connected to the pilot control and in signal communication with the FCC and operable to control action of the pilot control in response to the cue control signal.

A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.

A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.

An automated flying transport vehicle that capitalizes on the strengths and complexities of a fixed and rotary winged aircraft. The air transport vehicle comprises a body aerodynamically designed to generate lift and a plurality of rotors that can generate lift as well as forward thrust from which a fixed wing portion of the air transport vehicle will begin to generate additional lift allowing for a sustained flight.

An automated flying transport vehicle that capitalizes on the strengths and complexities of a fixed and rotary winged aircraft. The air transport vehicle comprises a body aerodynamically designed to generate lift and a plurality of rotors that can generate lift as well as forward thrust from which a fixed wing portion of the air transport vehicle will begin to generate additional lift allowing for a sustained flight.

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.

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.