Disclosed is a pilot aircraft system control input arrangement for a light aircraft having primary flight controls, the pilot aircraft system control input arrangement integrated into an armrest for a pilot's seat, the armrest providing forearm support for a pilot and having integrated therein or associated therewith a primary flight control and wherein the pilot aircraft system control input arrangement is disposed to be reached by fingers of a pilot with their forearm resting on the armrest, the pilot system control input arrangement comprising: a numerical keypad interface for inputting data; a rotatable selector for inputting data; a function selector operable to switch the pilot input arrangement between at least two input functions that each enable the pilot input arrangement to receive a different type of input, wherein the types of input for the at least two input functions are selected from at least two of the following input categories: a pressure setting for an altimeter; a transponder code for a transponder; a frequency for radio or navigation equipment; a course or heading for an autopilot or navigation equipment; an interfacing arrangement for communicating inputs to at least two aircraft systems selected from: an altimeter; a transponder; a radio; a navigation system; and an autopilot system.

The present invention relates to a control input device applicable to an eVTOL aircraft, which is an electric-powered vertical take-off and landing aircraft, and more particularly, to an aircraft control input device that may replace a cyclic control stick, a tail rotor control pedal, and a collective control stick used for flight control of a conventional aircraft, which is simpler in configuration and easier to operate than conventional control devices and may improve pilot convenience and stability of flight operation through simple and accurate flight manipulation, and a command input method using the same.

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.

Methods and systems for adjusting a force feel profile of an inceptor of an aircraft are provided. The force feel profile is based on a baseline value of an operating parameter of the aircraft and defines an amount of resistive force applied to the inceptor as a function of displacement of the inceptor. An embodiment of the method includes receiving data indicative of a current value of the operating parameter. Based on a difference between the current value and the baseline value of the operating parameter, a portion of the force feel profile corresponding to a range of displacement values is shifted to adjust an amount of resistive force defined by the portion of the force feel profile for the range of displacement values.

A portable cockpit seat apparatus, the apparatus including a portable cockpit seat, wherein the portable cockpit seat includes a hinge and has a stowed position, wherein the portable cockpit seat is folded about the hinge. The apparatus further including a headset including a display, and at least a flight control communicatively connected to the headset. The headset configured to and display a cockpit view of an aircraft. The flight control of the at least a flight control is connected to the portable cockpit seat and the at least a flight control, in response to actuation by a user, is configured to send a thrust signal, wherein the thrust signal causes the aircraft to alter its thrust and send a lift signal, wherein the lift signal causes the aircraft to alter its lift.

Methods and systems for adjusting a force feel profile of an inceptor of an aircraft are provided. The force feel profile is based on a baseline value of an operating parameter of the aircraft and defines an amount of resistive force applied to the inceptor as a function of displacement of the inceptor. An embodiment of the method includes receiving data indicative of a current value of the operating parameter. Based on a difference between the current value and the baseline value of the operating parameter, a portion of the force feel profile corresponding to a range of displacement values is shifted to adjust an amount of resistive force defined by the portion of the force feel profile for the range of displacement values.

A system for flight control of an electric vertical takeoff and landing (eVTOL) aircraft. The system generally includes a pilot control, a pusher component, a lift component and a flight controller. The pilot control is mechanically coupled to the eVTOL aircraft. The pilot control is configured to transmit an input datum. The pusher component is mechanically coupled to the eVTOL aircraft. The lift component is mechanically coupled to the eVTOL aircraft. The flight controller is communicatively connected to the pilot control. The flight controller is configured to receive the input datum from the pilot control, initiate operation of the pusher component, and terminate operation of the lift component. A method for flight control of an eVTOL aircraft is also provided.

A three-dimensional directional control assembly for a dual-mode aircraft, wherein the aircraft is capable of vertical and forward thrust. The assembly comprising a support structure, wherein the support structure is coupled to a dual-mode aircraft. The assembly further comprises a control stick coupled to support structure, wherein the control stick having a length and radius is configured to be manipulated along a plurality of axes, wherein the manipulation of the control stick produces an electronic signal. The assembly further comprises a first interface device disposed on the control stick configured to receive an interaction and enable a thrust element to spin as a function of the interaction. The assembly further comprises a second interface device, wherein the second interface is configured to receive an interaction and disable the thrust element as a function of the interaction.

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.

A control system (400) for an active inceptor (103) for a fly by wire aircraft permits a zero force null point to settle to a non-zero displacement trim position. An internal position state of a second order mass spring damper model is moved in conjunction with force-displacement characteristic coordinates. This results in no second order dynamics being superimposed on the feel of the inceptor (103) when dynamically adjusting the trim position, thereby eliminating the possibility of any unpleasant buzzing been felt by the operator of the inceptor during a trimming operation.