Aircraft, fly-by-wire systems, and controllers are provided. An aircraft includes a trim control system and a fly-by-wire system. The trim control system is configured for controlling surfaces of the aircraft. The fly-by-wire system is communicatively coupled with the trim control system and includes an input device and a controller. The input device is configured to receive a re-trim input from a user. The controller is communicatively coupled with the input device and is configured to control the trim control system, to obtain the re-trim input from the user, and to set a pitch trim of the aircraft based on a stable flight condition at a present airspeed of the aircraft in response to the re-trim input from the input device.

A redundant and dissimilar system for monitoring the status of contactors of an aircraft control stick. This monitoring system comprises at least one electrical power source, at least one processor and several circuits for monitoring the status of the switches of the contactors. Each monitoring circuit comprises and electrical power source, a switch for each contactor, the switches of a contactor being connected to each other, and an electronic assembly provided with receivers arranged in series with each other. Each switch is arranged in parallel with at least one receiver so as to short-circuit the at least one receiver when the switch is in the closed state. Each processor measures and analyses an electrical feature of the electronic assembly, such as a mains voltage VE as the terminals of the electronics assembly, in order to determine the status of each switch.

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.

Systems and methods for controlling a fixed-wing aircraft during flight are disclosed. The aircraft comprises first and second flight control surfaces of different types. The method comprises determining that a pilot command of the first flight control surface will excite a structural flexible mode of the aircraft and then executing the pilot command of the first flight control surface in conjunction with a command of the second flight control surface to mitigate the effect of the excitation of the structural flexible mode of the aircraft.

Aircraft control systems to enable shared input controls. A single inceptor may provide outputs to control both land-based aircraft controls and air-based aircraft controls to reduce the number of inceptors required. In an example a side-stick provides control of both pitch and aircraft nose-wheel steering. Active inceptor technology may be utilised to provide feedback to the operator on the control system state.

An aircraft (101) is provided with a single centrally located inceptor (110) for controlling pitch and roll of the aircraft. The inceptor (110) is provided with a double grip (11, 112) so that it may be comfortably operated by either a pilot or a co-pilot. A central location for the inceptor ensures that its motion and position is visible to both pilot and co-pilot. Not only is this a benefit from a safety point of view but also during pilot training. Alternatively, two inceptors (411, 412) are provided in the centre console (406) adjacent to one another for operation respectively by the pilot and co-pilot and may be mechanically linked. Optionally, the aircraft may be provided with outboard throttle quadrants (117, 118) for operation respectively by the co-pilot and pilot. The outboard throttle quadrants may be mechanically linked together.

A sensor system and a joystick including the sensor system. The sensor system comprises a magnetic field sensor, and first and second magnetic sources. The first magnetic source is rotatable relative to a sensitive surface of the sensor and generates a first magnetic field contribution of at least quadrupolar order. The second magnetic source is pivotable with respect to the sensitive surface and generates a second magnetic field contribution. The sensor is configured for detecting at least an in-plane component of a superimposition field of the first and second magnetic contributions at a plurality of lateral measurement locations on the sensitive surface, obtaining measurements, and determining a rotation angle for the first source from the field gradient measurements and two angular directions for the second source from the field mean measurements. Lateral measurement locations are arranged into two pairs of diametrically opposite measurement locations with respect to the sensitive surface.

A first hand control controls an altitude of a vertical takeoff and landing (VTOL) aircraft; the movement of the VTOL aircraft within a plane defined by a roll axis and a pitch axis is independent of the first hand control. The first hand control is provided on a first hand side of a pilot's seat included in the VTOL aircraft. A second hand control controls the movement of the VTOL aircraft within the plane defined by the roll axis and the pitch axis; the altitude of the VTOL aircraft is independent of the second hand control. The second hand control is provided on a second hand side of the pilot's seat that is opposite from the first hand side.

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.

Disclosed is a pitch and roll control arrangement for controlling both lateral and longitudinal orientation of an aircraft having at least one pilots seat, wherein the control arrangement comprises a handle (5110) positionable substantially above the pilot's seat and shaped to be gripped by a pilot (10); an elongate connector (5112) that extends in a generally forward direction from the handle portion to a forward joint; an elongate transverse arm (5116) extending generally transversely from the forward joint of the connector to a mounting location forward and to the side of the pilot in use; a mounting arrangement configured to support the transverse arm at the mounting location to permit the transverse arm to move laterally sideways and fore and aft and to constrain the forward joint to move generally horizontally as the handle is moved fore and aft and laterally by the pilot; a control coupling associated with the mounting arrangement arranged to provide at least one moving connection which moves in response to fore and aft movement and lateral movement of the handle for coupling to actuators of the aircraft.