Aspects relate to a connector and methods of use for charging an electric aircraft. An exemplary connector includes a housing configured to mate with a port of an electric aircraft, where the housing includes a fastener for removable attachment with the electric aircraft port, at least a high-voltage conductor configured to conduct a high-voltage electrical power, at least a low-voltage conductor, configured to conduct a low-voltage electrical power, at least a control signal conductor configured to conduct a control signal, at least a ground conductor configured to conduct to a ground, at least a cooling channel configured to contain a flow of a coolant, and at least a proximity signal conductor configured to conduct a proximity signal indicative of attachment with the electric aircraft port when the housing is mated with the port.

An apparatus for venting battery ejecta for use in an electric aircraft is presented. The apparatus includes a battery module with a plurality of electrochemical cells. The electrochemical cells of the plurality of electrochemical cells are separated by a carbon fiber barrier. Venting port of a plurality of venting ports is configured to vent an electrochemical cell of the plurality of electrochemical cells using a venting path of a plurality of venting paths, wherein the plurality of vent ports is fluidly connected to the plurality of venting paths and the plurality of venting paths are fluidly connected to at least an outlet. Venting paths direct the battery ejecta from the electrochemical cell to the outside of the electric aircraft through at least an outlet.

A system for restricting power to a load to prevent engaging circuit protection device for an aircraft. The system includes an energy source of an aircraft. The system further includes a plurality of sensors configured to sense at least an electrical parameter of a load of the plurality of loads. The system further includes an aircraft controller configured to receive electrical parameter of a load of the plurality of loads from the plurality of sensors, compare the electrical parameter to at least a current allocation threshold, detect that the electrical parameter has reached the current allocation threshold, calculate a power reduction to the load, and reduce power from the at least an energy source to each load of the plurality of loads by the power reduction. The system further includes at least an electrical circuit of an aircraft, wherein the electrical circuit comprises a circuit protection device.

A system for managing residual energy for an electric aircraft, wherein the system includes a battery pack incorporated in the electric aircraft, wherein the battery pack includes a plurality of battery modules and at least a pack monitor unit configured to generate a battery pack datum. The system further includes a charging component connected to the battery pack and a sensor connected to the charging component and configured to detect at least an electrical parameter of the charging component and the electric aircraft and generate a residual datum as a function of the at least an electrical parameter and the battery pack datum. The system further includes a computing device configured to receive the residual datum from the sensor, identify a residual element, generate an alert datum as a function of the residual element, and execute a security measure as a function of the alert datum.

An aerial vehicle adapted for vertical takeoff and landing using pivoting thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to takeoff with thrust units providing vertical thrust and then transitioning to a horizontal flight path. An aerial vehicle with pivoting thrust units with propellers, wherein some or all of the propellers are able to be stowed and fully nested during forward flight. An aerial vehicle able to quickly alter its thrust. A quick reaction propeller system which alters the pitch of the propeller blades in response to changes in coning angle of the propeller.

In an aspect, a system for displaying synoptic information is provided. A processor of the system may retrieve and/or receive operation data related to the use of a corresponding electric aircraft. Operation data may be displayed on a display of the system using one or more visual representations or audio presentations.

The invention relates to a flight unit for a vertical take-off and landing aircraft with a plurality of drive units arranged on a wing assembly, wherein the wing assembly comprises longitudinally extended wing assembly struts connected to one another at node points. According to the invention, a certain number of the wing assembly struts each comprise at least one wing with aerofoil form, which wing is arranged or configured for rotation in a longitudinal section of the wing assembly strut which extends longitudinally between two nodes.

A VTOL aircraft (1), including: a fuselage (2) for transporting passengers and/or load; a front wing (3) attached to the fuselage (2); an aft wing (4) attached to the fuselage (2), behind the front wing (3) in a direction of forward flight (FF); a right connecting beam (5a) and a left connecting beam (5b), which connecting beams (5a, 5b) structurally connect the front wing (3) and the aft wing (4), which connecting beams (5a, 5b) are spaced apart from the fuselage (2); and at least two propulsion units (6) on each one of the connecting beams (5a, 5b). The propulsion units (6) include at least one propeller (6b, 6b) and at least one motor (6a) driving the propeller (6b, 6b), preferably an electric motor, and are arranged with their respective propeller axis in an essentially vertical orientation (z).

An integrated electric propulsion assembly includes a stator including at least a first magnetic element generating first magnetic field. The assembly includes a propulsor with an integrated rotor, the propulsor further including a hub rotatably mounted to the stator and at least a second magnetic element affixed to the hub, the at least a second magnetic element generating a second magnetic field. At least one of the first magnetic field and the second magnetic field varies with respect to time, wherein the varied magnetic field includes generating a magnetic force between the at least a first magnetic element and the at least a second magnetic element, and the magnetic force causes the hub to rotate with respect to the stator.

A reciprocating lift and thrust system include at least an airfoil and a reciprocating driver configured to produce a reciprocating motion of the airfoil. The system may further include a control unit to change or maintain a suitable angle of attack of the airfoil for lift or thrust as well as to facilitate the cyclic control of the flying vehicle driven by the reciprocating system. The lift and thrust system may be deployed in a module that includes at least two reciprocating airfoils (RAs) and is configured to substantially cancel out the inertia forces and moments associated with the individual airfoils. The reciprocating driver maybe, but not limited to, a mechanical, electromagnetic, electrical, or hydraulic driver. The embodiments of the subject invention provide novel and advantageous RA-driven aircraft, RA-driven flying motor vehicles, and RA-driven watercraft.