A control system for an aircraft, the system including a pilot input device configured to receive a pilot input, a plurality of sensors, each of the plurality of sensors positioned on a corresponding landing gear of the aircraft and configured to sense a parameter on the corresponding landing gear, and a controller in communication with the plurality of sensors, the controller configured to calculate an output command based on the pilot input and the sensed parameters of the landing gear, the output command including instructions for controlling a rotor of the aircraft.

A control system for an aircraft, the system including a pilot input device configured to receive a pilot input, a plurality of sensors, each of the plurality of sensors positioned on a corresponding landing gear of the aircraft and configured to sense a parameter on the corresponding landing gear, and a controller in communication with the plurality of sensors, the controller configured to calculate an output command based on the pilot input and the sensed parameters of the landing gear, the output command including instructions for controlling a rotor of the aircraft.

The present invention relates to a force application device for a control stick of an aircraft comprising a shaft and a control lever configured to rotate the shaft about a first axis, the device comprising: a magnetic brake comprising a braking part configured to be connected to the shaft, and a volume containing a rheological fluid in contact with the braking part, of variable shear resistance as a function of a magnetic field applied to the rheological fluid, a force feedback motor configured to exert a resistive force opposing the rotation of the shaft about the first axis, a motor power source, a movable magnetic element biased towards a position close to the magnetic brake, and distancing means configured to maintain the movable magnetic element in a position away from the magnetic brake, when such distancing means are powered by the power source.

An assembly comprising a first part and a second part, the assembly comprising a disconnectable coupling system provided with a mechanical fuse for securing the first part and the second part according to an axis of movement up to a breaking threshold. The assembly comprises at least one single-use friction brake interposed between the first part and the second part, the friction brake braking a movement of the first part with respect to the second part after the mechanical fuse has broken.

A pivot assembly for a control lever. The pivot assembly include a primary pivot bearing arranged about a longitudinal axis (A) and a redundant pivot bearing arranged about the longitudinal axis (A). The redundant pivot bearing is configured to become operative as a bearing in the event that the primary pivot bearing malfunctions, and to produce haptic feedback in the control lever throughout operation of the redundant pivot bearing.

A command device for controlling a mechanical energy reduction assembly of an aircraft, movable between an inactive configuration and a maximum mechanical energy reduction configuration, includes a rocker button, movable between a mechanical energy reduction assembly configuration maintaining position, a first position of incremental movement of the mechanical energy reduction assembly to its maximum mechanical energy reduction configuration and a second position of incremental movement of the mechanical energy reduction assembly to its inactive configuration. The command device further includes at least one return element configured to return the rocker button to its maintaining position.

A control system is for a high lift assembly of an aircraft. The assembly is controllable in two aerodynamic configurations each with different lift. The control system includes a manual control device operable by a pilot of the aircraft. The manual control device includes at least one member movable relative to a base body. The movable member can be moved relative to the base body between a rest position, a first position and a second distinct position. The manual control device includes a resilient return device for the movable member in the rest position. The manual control device issues a signal when the movable member reaches either the first or second position, to move the high lift assembly between two of the aerodynamic configurations.

A control system of an air vehicle for urban air mobility (UAM) is provided. A human-machine interface (HMI) system enables people to more easily control the air vehicle for UAM with a familiar method. The control system includes a steeling wheel operated for steering of the air vehicle, an accelerator pedal operated for acceleration of the air vehicle, and a decelerator pedal operated for deceleration and braking of the air vehicle. An altitude designating device selects and designates a target altitude and a controller generates a control command for adjusting altitude, acceleration, deceleration and braking, and steering of the air vehicle, based on air vehicle driving information. A drive device is then operated according to the control command generated from the controller.

A control lever assembly for controlling an aircraft system. The lever includes: a housing having an outer side and an aperture defined by a rim; and a control lever extending through the aperture and movable in the aperture; the control lever having an outer cover member arranged to slide over the outer side of the housing and cover the rim throughout the range of movement of the control lever.

An actuation system for an aircraft can include an actuator and a plurality of clutches connected to and structured to be moved by the actuator. The actuation system can include a plurality of control levers connected to the plurality of clutches and structured to be moved by the plurality of clutches when the plurality of clutches are moved by the actuator. The actuation system can include a processor connected to the actuator and to the plurality of clutches. The processor can identify one or more clutches connected to one or more control levers of the plurality of control levers for controlling an operation of the aircraft, and cause the one or more clutches connected to the one or more control levers to be in an engaged stat. The processor can activate the actuator to cause movement of the one or more control levers via the one or more clutches.