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.

The invention relates to an aircraft flight control column device (1) comprising: a casing (2) for attaching to an aircraft structure; an output shaft (3) for connecting to a flight control column (56), the output shaft (3) being mounted such that it rotates in relation to the casing (2); a primary group (4) comprising a first torque-generating body (7, 8) for applying a first torque to the output shaft (3); a secondary group (5) comprising a second torque-generating body (7, 8) for applying a second torque to the output shaft (3); and a clutch for selectively connecting the primary group (4) and the secondary group (5) to the output shaft (3).

An oscillation system comprises 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.

An aircraft control system includes: a motor with a rotating shaft; a pilot control input; a linear actuator connecting the pilot control input to the rotating shaft; a sensor identifying a position of the pilot control input; and a transmitter transmitting the pilot control input position to a controller, the controller adjusting an aircraft performance device based on the received pilot control input position.

An aircraft inceptor system includes an inceptor member arranged to be operated by a user to cause a corresponding movement of a moveable aircraft surface. The system also includes means for detecting the operation of the inceptor member by the user and for providing a movement signal, associated with the detected operation, to a flight control computer, the flight control computer providing a control signal to an actuator to move the aircraft surface according to the movement signal. The means for detecting the operation of the inceptor member by the user comprises a force sensor configured to sense the force applied by the user to the inceptor member, the movement signal being derived based on the sensed force.

The invention relates to a force application device for a control stick of an aircraft, said stick comprising a control lever that is connected to a motor comprising a drive shaft, said device having: a first pin connected to the drive shaft, a housing, a second pin secured to the housing, an electromagnet secured in relation to the housing, a movable actuator which comprises a magnetic material such that said actuator can be displaced depending on a supply of current of the electromagnet, and means for clamping the first pin and the second pin which comprise a first tooth and a second tooth, said device having an operating configuration in which the electromagnet is active and the actuator separates the teeth away from the first pin and the second pin, and a blocking configuration in which the electromagnet is inactive, with the first tooth and the second tooth coming into contact with the first pin and the second pin.

In one or more embodiments, a method for providing continuously variable feel forces for an aircraft comprises sensing, by each of at least one sensor associated with at least one aircraft control, a force sensor value. The method further comprises determining a net force value by using the force sensor value for each of at least one sensor. Also, the method comprises comparing the net force value to a desired breakout force. In addition, the method comprises determining whether the net force value exceeds the desired breakout force. Additionally, the method comprises determining an adjusted force value by using the desired breakout force and the net force value, when the net force value exceeds the desired breakout force. Also, the method comprises determining an actuator torque command based on the adjusted force value. Further, the method comprises commanding an autopilot actuator with the actuator torque command to apply torque.

This document details a series of inventions relating to the design and optimization of hybrid-to-electric aircraft. In particular, a system and method is presented to improve the effectiveness of mixed aerodynamic control surfaces which are actuated by a novel electromechanical actuator which allows the system to be tolerant to actuator faults and jams. In addition, innovations relating to integration and quick swap of large energy storage units such as batteries are disclosed, and further, an algorithm which may be used to optimize numerous aspects of the regional hybrid-to-electric aircraft known as Total Cost Door to Door or TCD2D.

The present invention relates to a force application device for a control stick of an aircraft, wherein the control stick comprises a control lever (1) rotating a shaft (A1) about a first axis (A), the device comprising a magnetic brake (5a) which comprises a magnetisable element (50a) mounted on the shaft and a magnetic transmitter (51a) which is opposite the magnetisable element and free to rotate about the first axis relative to the magnetisable element, the magnetic transmitter having an activated state in which the magnetic transmitter is supplied with current and generates a magnetic field in a volume occupied by the magnetisable element, and a deactivated state in which the magnetic transmitter is not supplied with current and does not generate a magnetic field, so as to prevent the magnetisable element from rotating about the shaft relative to the magnetic transmitter.

The present invention relates to a force application device for a control stick of an aircraft, wherein the control stick comprises a control lever (1) rotating a shaft (A1) about a first axis (A), the device comprising a magnetic brake (5a) which comprises a magnetisable element (50a) mounted on the shaft and a magnetic transmitter (51a) which is opposite the magnetisable element and free to rotate about the first axis relative to the magnetisable element, the magnetic transmitter having an activated state in which the magnetic transmitter is supplied with current and generates a magnetic field in a volume occupied by the magnetisable element, and a deactivated state in which the magnetic transmitter is not supplied with current and does not generate a magnetic field, so as to prevent the magnetisable element from rotating about the shaft relative to the magnetic transmitter.