An interconnected flight controller for an aircraft includes a mechanical linkage connecting a pilot interface with a copilot interface. When an input is provided to either of the pilot or copilot interfaces, coordinated motion is provided between them of a proportional magnitude and direction. A mechanical-disconnect element within the mechanical linkage is adapted to actuate mechanical decoupling between the pilot interface and the copilot interface. One or more sensors is coupled to the mechanical linkage to sense inputs and communicate the inputs to a fly-by-wire flight controller. An autopilot servo is coupled to the mechanical linkage for providing autopilot control or feedback and a force-feedback subsystem is connected to the mechanical linkage to simulate and apply an opposing force of aircraft control surfaces to the pilot interface and the copilot interface.

A compact electromechanical decoupler device is operatively connected between a manual control device of an aircraft and an electromechanical actuator that controls the flight modes of the aircraft. The electromechanical decoupler device is operable to decouple the operative connection between the manual control device and the electromechanical actuator with the absence of power supplied to the electromechanical decoupler device. The electromechanical decoupler device can recouple the operative connection between the manual control device and the electromechanical actuator on resupply of power to the electromechanical decoupler device and on manually achieving proper rotational alignment or indexing between the mechanical control device and the electromechanical actuator.

A flight control computer (FCC) for a rotorcraft includes a processor and a non-transitory computer-readable storage medium storing a program to be executed by the processor, with the program including instructions for providing main rotor overspeed protection. The instructions for providing the main rotor overspeed protection include instructions for monitoring sensor signals indicating a main rotor RPM, determining a target operating parameter, determining one or more flight parameters in response to a relationship between the main rotor RPM and the target operating parameter indicating a main rotor overspeed condition. Determining the one or more flight parameters includes determining a setting for a flight control device of the rotorcraft that changes the main rotor RPM, controlling positioning of a pilot control according to the flight parameters, and controlling the flight control device of the rotorcraft according to positioning of the pilot control.

According to one embodiment, a pilot assistance system includes a trim assembly and a trim assembly control system. The trim assembly is operable to communicate with a pilot control device and operable to apply a force against the pilot control device in resistance of a command received from a pilot via the pilot control device. The trim assembly control system is in communication with the trim assembly, configured to identify a first pilot control device position relative to a reference pilot control device position, and configured to instruct the trim assembly to apply a cueing force against the pilot control device if the pilot control device is positioned proximate to the first pilot control device position.

A method of using a tactile signal warning device forming part of a human-operated flight control member of a rotorcraft. The warning device makes use of an anchorable motorized trim actuator for generating a resisting force against movement of the flight control member. The warning device comprises a warning unit that, as a function of a power margin (MP1) calculated by a predictor unit in compliance with a current regulation rating of the power plant and on condition that state data indicates that an autopilot is activated in a higher operating mode, acts to generate an order to activate the trim actuator depending on the conditions under which the flight control member is being moved as identified by a force management unit.

A rotorcraft autopilot system includes a series actuator connecting a cockpit control component to a swashplate of a rotorcraft, the series actuator to modify a control input from the cockpit control component to the swashplate through a downstream control component. The rotorcraft autopilot system also includes a differential friction system connected to the cockpit control component, the differential friction system to control the series actuator to automatically adjust a position of the cockpit control component during rotorcraft flight based, in part, on a flight mode of the rotorcraft.

The invention relates to a flight control device for an aircraft, the device comprising a mount, a lever pivotally mounted on the mount, and mechanical means for generating a return force for the lever, said means including a spring and a first motor member that are arranged so that a first end of the spring is constrained to move in rotation with the lever and a second end of the spring is constrained to move in rotation with an outlet shaft of the first motor member. According to the invention, the flight control device includes an electrical assistance system for assisting said mechanical means for generating a return force.

An active inceptor apparatus and method for operating a machine. The apparatus comprises a stick member having a grip portion, the stick member being pivotably mounted relative to a housing. It further comprises a position sensor responsive to, and for generating signals indicative of, stick member position. A force sensor is provided on the stick member responsive to, and for generating signals indicative of, force applied to the stick by a user. The apparatus also includes a control unit operable to receive the position and force signals from the position and force sensors respectively. The control unit is operable to process the signals according to a predetermined relationship to determine a value FD indicative of force applied to the stick member relative to displacement of the stick member. The control unit is also operable to generate machine control signals as a function of position signals and force signals in dependence upon the value FD, for communication to the machine.

Automatic flight control actuator systems are provided. In one example, the system includes a pilot input linkage that receives an input and a flight surface output linkage adapted to control a flight surface. The system also includes a strain wave gear including a flex spline coupled to one of the pilot input linkage and the flight surface output linkage. The strain wave gear further includes a circular spline coupled to the other of the flight surface output linkage and the pilot input linkage, and coupled to the flex spline such that the input from the pilot input linkage is transferred to the flight surface output linkage via the strain wave gear.

According to one embodiment, a pilot assistance system includes a trim assembly and a trim assembly control system. The trim assembly is operable to communicate with a pilot control device and operable to apply a force against the pilot control device in resistance of a command received from a pilot via the pilot control device. The trim assembly control system is in communication with the trim assembly, configured to identify a first pilot control device position relative to a reference pilot control device position, and configured to instruct the trim assembly to apply a cueing force against the pilot control device if the pilot control device is positioned proximate to the first pilot control device position.