A system of fall back flight control configured for use in electric aircraft includes an input control configured to receive a pilot input and generate a control datum. System includes a flight controller communicatively coupled to the input control and configured to receive the control datum and generate an output datum. The system includes the actuator having a primary mode in which the actuator is configured to move the at least a portion of the electric aircraft as a function of the output datum and a fall back mode in which the actuator is configured to move the at least a portion of the aircraft as a function of the control datum. The actuator configured to receive the control datum, receive the output datum, detect a loss of communication with the flight controller, and select the fall back mode as a function of the detection.

A multiplexer switching device is described herein comprising a first data network comprising a plurality of NO contacts; and a second data network comprising a plurality of NC contacts; wherein said a first data network is connected to said second data network via a common DC voltage link.

An aircraft having an augmented reality flight control system integrated with and operable from the pilot seat and an associated pilot headgear unit, wherein the flight control system is supplemented by flight-assisting artificial intelligence and geo-location systems is presented. The present disclosure includes an augmented reality flight control system incorporating real-world objects with virtual elements to provide relevant data to a pilot during aircraft flight. A translucent substrate is disposed in the pilot's field of view such that the pilot can see therethrough, and observe virtual elements displayed on the substrate. The system includes a headgear that is worn by the pilot. A flight assistance module is configured to receive data related to the aircraft and provide predictive assistance to the pilot during flight based on the received data based in part on a pilot profile having preferences related to the pilot.

A unit that is mountable to an underside of drone to attach an attachment to the drone and then release the attachment after the drone is airborne. The unit is provide with a retractable bar that is controllable via a remote controller. In use, an attachment is suspended from the bar and once the drone becomes airborne, a user may retract the bar via remote control to drop the attachment previously suspended from the bar.

The present invention achieves technical advantages as a vehicle cabin, comprising a floor system formed of removable and reconfigurable floor segments extending from a vehicle frame, and a ceiling system formed of removable and reconfigurable ceiling segments disposed in the ceiling of the vehicle cabin. Floor segments that can be positioned to form a floor channel, therebetween. A fixture interface adapted to releasably secure a fixture to the floor system. The fixture can be slidably repositioned within the vehicle along the floor channel. One of the ceiling segments includes one or more of a lighting module, a ventilation outlet, a ventilation inlet, a display screen, or a touch control panel. The ceiling segments can be hexagonal.

Disclosed is a ground movement system for a helicopter having a fuselage and rotor blades fixed to the top of the fuselage, the ground movement system comprising at least three wheels secured below the fuselage of the helicopter, the wheels being retractable during flight; a motor positioned in the hub or on the undercarriage leg of each of at least two of the wheels, wherein each motor is operable to rotate the wheel in forward and backward directions; wherein each motor allows the wheel to rotate freely when unpowered; at least one user interface operable to receive user input commands to control the speed and direction of travel of the helicopter using the ground movement system; and a control arrangement to provide control signals to each of the motors based on the user input commands.

A piloting device for piloting an aircraft includes a piloting member suitable for being actuated by a pilot, a mechanism for mounting and guiding in rotation the piloting member about at least one rotation axis with respect to a frame, at least one force sensor connected between the piloting member. The mechanism includes at least one sensing element configured to produce a signal upon deformation indicative of a force applied to the piloting member. The force sensor comprises at least one pair of bearing surfaces. The device also includes at least one pair of stops configured to limit the angular amplitude of rotation of the piloting member with respect to the frame on abutment of the at least one pair of bearing surfaces with at least one pair of stops. The stops or at least one of the bearing surfaces comprises a compliant material.

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.

A control system for an aircraft allowing a pilot of the aircraft to control aerodynamic means, the control system comprising a processing unit for generating control commands, the control commands being transmitted to control devices to modify a position of the aerodynamic means and to pilot the aircraft according to four control axes having a pitch control axis, a roll control axis, a yaw movement control axis and a lift control axis, the control system comprising a control member generating control setpoints, the control setpoints being transmitted to the processing unit generating the control commands under the dependency of the control setpoints, the control member being mechanically disconnected from the control devices.

A vertical takeoff and landing aircraft takeoff/land as a multirotor and cruises as an airplane. The aircraft comprises two major parts: a winged carrier frame comprises wings, engines, propellers and landing gears; a tilting fuselage comprises cockpit, cabin and tail. The winged carrier frame is basically an X/H frame multirotor in which its thruster carrying arms are wing shaped. The aircraft can vertical takeoff as a multirotor aircraft after gaining safe altitude and forward airspeed the aircraft changes its flying axis that the wings and the thrust direction parallel to the horizon. The lift generated by the wings and thrust generated by the thrusters that aircraft has basic airplane flying characteristics. The fuselage tilted to keep the crew, passengers and payload relatively parallel to the horizon. The speed is reduced then the winged carrier frame and the tilting fuselage returned to multirotor mode for the landing.