A control device includes :a resultant thrust magnitude calculation unit that calculates a magnitude of a resultant thrust of a vertical thrust and a horizontal thrust, based on a magnitude of a thrust indicated by a signal output from a thrust adjustment lever; a resultant thrust angle setting unit that sets a resultant thrust angle in accordance with a speed of an aircraft; a component calculation unit that calculates a vertical component and a horizontal component of the resultant thrust; and a rotor control unit that controls a vertical rotor device to provide the vertical thrust having the vertical component and controls a horizontal rotor device to provide the horizontal thrust having the horizontal component.

A power supply system includes: a power converter for converting electric power of any one of a plurality of batteries and supplying the converted electric power to one or more second loads; a switch capable of selectively connecting any one of the plurality of batteries to the power converter; and a controller for comparing remaining capacities of the respective batteries, and when the difference between the highest remaining capacity and the lowest remaining capacity exceeds a predetermined threshold, controlling the switch to connect the power converter to the battery having the highest remaining capacity.

Vertical short takeoff and landing (VSTOL) aircraft include primary airfoils extending outwardly from a forward region of the aircraft fuselage, and secondary empennage airfoils extending outwardly from an aft region of the aircraft fuselage so as to be separated from the forward primary airfoils and thereby define a space therebetween which accommodates non-cyclic controllable propellers operably driven by a respective engine of a propulsion unit. The propulsion units are mounted for pivotal movement within the defined space between the primary airfoil and the secondary empennage airfoils so as to achieve a first operational position wherein the thrust line of the propellers is orientated substantially parallel to the longitudinal axis of the fuselage and a second operational position wherein the thrust line of the propellers is oriented substantially perpendicular to the longitudinal axis of the aircraft. The propulsion units may be mounted aft of the aircraft center of gravity (CG).

A system for swarm communication for an electric aircraft fleet, wherein the system includes a plurality of electric aircrafts connected by a mesh network. The system further includes a computing device communicatively connected to the mesh network, wherein the computing device includes an authentication module configured to authenticate each electric aircraft and facilitate communication of a plurality of aircraft data between the plurality of electric aircrafts. The computing device includes a plurality of communication components, each assigned to an electric aircraft of the electric aircraft fleet, wherein each communication component is configured to transmit the aircraft data to the communication component of its assigned electric aircraft. The system further includes a cloud database configured to record the plurality of aircraft data.

An electric propulsion system for a vertical takeoff-and-landing aircraft having an inverter assembly, a gearbox assembly, an electric motor assembly. The inverter assembly, the gearbox assembly, and the electric motor assembly may be substantially aligned along an axis. The inverter assembly, a gearbox assembly, and electric motor assembly may each abut at least one of the others. The electric engine may use a liquid, such as oil, for cooling and lubricating components of the inverter assembly, gearbox assembly, and electric motor assembly. Further, the electric engine may use volumes of oil for cooling and lubricating components below a threshold volume so that the electric engines do not require a fire protective barrier.

A system includes a frame and a plurality of machines mounted on the frame, wherein each machine of the plurality of machines includes an actuator, and wherein each machine is configured to operate in a defined condition. The system further includes at least one controller configured to control the actuators so as to exert an excitation of each machine of the plurality of machines. The system further includes at least one sensor configured to measure at least one response indicator of a response of the system to the excitations of the plurality of machines. The system further includes a diagnosis system configured to receive the at least one measured response indicator.

A system for emergency shutdown of an electric charger using a de-energizing protocol is presented. The system includes a computing device, wherein the computing device is configured to receive a sensor datum from a sensor, determine a disruption element between a charging connector and an electric vehicle as a function of the sensor datum, and initiate a de-energizing protocol as a function of the disruption element.

An electrical power system includes an electrical machine having one or more windings and an AC-DC power electronics converter including a commutation cell having a power circuit and a gate driver circuit. The power circuit includes a plurality of power semiconductor switching elements and a capacitor. The gate driver circuit is electrically connected to and configured to provide switching signals to a gate terminal of each power semiconductor switching element. A peak rated power output of the electrical machine and the AC-DC power electronics converter is greater than 25 kW, a maximum efficiency of the AC-DC power electronics converter is greater than 97%, and a value of parameter β is greater than or equal to 0.3 PV/s.sup.2, where β is a product of a maximum switching frequency of the switching signals and a maximum rate of change of a source-drain voltage of the plurality of power semiconductor switching elements.

VERTICAL TAKE-OFF AIR VEHICLE WITH BLENDED AIRFOIL FUSELAGE AND WINGS, object of this application, essentially consists of a fixed-wing aircraft comprised of an airfoil-shaped fuselage (02) with four wings (10) shaped by the same airfoil. Accordingly, the fuselage has an aerodynamic wing behavior contributing to lift and minimizing drag of the aircraft, which provides greater payload and greater flight autonomy, in addition to good flight safety due to gliding during the horizontal flight. On each wing tip there is installed a thruster (35) (electric, ducted fan, turbojet/fan, or even a propeller) capable of turning, tilting longitudinally relative to the shaft of the aircraft, independently, by means of a rotary control system of the thrusters (35). This system is comprised of a driveshaft (34) installed on each wing and its corresponding electric motor (30). The thrusters (35) are all identical in performance, weight, and size, as a form of minimizing manufacturing costs, but the thrusters of the wings to the left rotate in a counter direction to those of the wings to the right to stabilize (neutralize) the wing tip vortex effect and torque due to the rotary moments caused by the rotary set of each thruster. A single control center commands both the rotation of the thrusters and the traction thereof, providing total control of the aircraft by vectoring and rotation, without the need to use control surfaces. The present model is innovative in its design generated from an airfoil that blends the entire fuselage and wings, presenting a hybrid behavior, as it performs the tasks of a VTOL vehicle, of a helicopter, as well as a conventional fixed-wing aircraft, being versatile in its abilities of vertical landing/take-off, gliding, vertical flight forwards and backwards, and horizontal flight with maximum economy.

Systems and methods relate to electric propulsor fault detection. An exemplary system includes at least a first inverter configured to accept a direct current and produce an alternating current, a first propulsor, a first motor operatively connected with the first propulsor and powered by the alternating current, and at least a noise monitoring circuit electrically connected with the direct current and configured to detect electromagnetic noise and disengage the at least an inverter as a function of the electromagnetic noise.