This aircraft flight compensator control system comprises a motor (3) and a variable-friction actuator (6) coupled with the motor and with an output shaft (8).

The variable-friction actuator comprises a variable-friction-torque magnetic clutch connected to the output shaft

Systems and methods for providing tactile feedback via an inceptor. A control system for an aircraft includes an inceptor and a controller. The inceptor includes a grip portion moveable between a plurality of positions and one or more motors to apply a variable force to the grip portion. The controller is coupled to the one or more motors. The controller includes an electronic processor and a memory. The controller is configured to operate in a first operating mode, select a first tactile feedback profile associated with the first operating mode, and control the one or more motors based on the first tactile feedback profile. The controller is further configured to detect a transition from the first operating mode to a second operating mode, select a second tactile feedback profile associated with the second operating mode, and control the one or more motors based on the second tactile feedback profile.

In accordance with an embodiment, a method of operating a rotorcraft includes transitioning from a first mode to a second mode when a velocity of the rotorcraft exceeds a first velocity threshold. Transitioning between the first and second modes includes fading out a gain of a dynamic controller over a first period of time, and decreasing a value of an integrator of the dynamic controller over a second period of time.

This aircraft flight trim system comprises a friction module that has variable friction and is coupled on one side to a drive shaft and on the other side to an output shaft via a kinematic chain.

It has a control circuit which controls the friction module on the basis of an angular displacement value of the output shaft provided by a position sensor and on the basis of a force feedback control signal provided by a flight control computer.

An inceptor apparatus for an aircraft comprises a primary inceptor member provided in the form of a stick member having a grip portion, at which the stick member can be gripped by a pilot's hand, and a secondary inceptor member provided at an upper portion of the primary inceptor member and having an actuating portion, at which the secondary inceptor member can be manually actuated by a pilot's thumb. Both inceptor members have associated a respective sensor assembly which is provided to generate electronic flight control signals or commands in response to at least one of i) pivoting movements of the respective inceptor member around each of two independent maneuvering axes associated to the inceptor member, ii) forces acting on or via the respective inceptor member in pivoting directions with respect to each of the maneuvering axes, and iii) lateral flexing or bending of the respective inceptor member.

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.

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.

An oscillation system includes an oscillation circuitry configured to cause at least one motor of a first set of motors to provide an oscillation of a user-input device in at least one axis of the user-input device. The oscillation may be triggered in response to an input from at least one sensor, the user-input device for operating an aircraft control system of an aircraft. The oscillation circuitry is configured to operate independently from a resistive force circuitry. The resistive force circuitry is to provide a resistive force to the user-input device, using the at least one motor of the first set of motors.

Electromechanical drive system (1) to control a transmission shaft (2) connected to the mechanical operating systems of an aircraft, comprising an electric machine (3), a two-way transmission rotation (8) and a clutch assembly (9) wherein the two-way transmission rotation (8) is configured, in any direction of rotation of the transmission shaft (2), to selectively allow the passage of torque either only between the electric machine (3) and the transmission shaft (2) when the torque is supplied by the electric machine (3) to the transmission shaft (2) or between the transmission shaft (2), the clutch assembly (9) and the electric machine (3) when the torque is supplied by the transmission shaft (2) to the electric machine (3).