A vertical take-off and landing aircraft is provided. The aircraft comprises a fuselage which has a nose end, a tail end, and a plurality of seats disposed in the interior. A pair of rear wings extend outwardly from opposing sides of the fuselage between a cockpit and the tail end, and a pair of front wings extend outwardly from opposing sides of the fuselage between the cockpit and the nose end. Each of the pair of rear wings and front wings includes an adjustably mounted turbine which comprises a statically mounted fan pod, a duct rotatably connected to the fan pod, and an adjustable nozzle rotatably connected to the duct. The nozzle can be adjusted to a variety of configurations ranging between a vertical position and a horizontal position via the duct. The adjustably mounted turbine enables the aircraft to adjust thrust through vectors ranging between horizontal and vertical.

A gimbaled rotor assembly for an aircraft. The gimbaled rotor assembly including a static mast; a spherical bearing comprising an inner component and an outer component pivotable relative to each other about a bearing focus, the inner component fixedly coupled to the static mast; a rotor hub rotatably coupled to the outer component, allowing for relative rotation of the rotor hub about a rotor axis and for pivoting together with the outer component about the bearing focus; and a primary hub spring coupling the outer component to the static mast and configured for opposing pivoting of the rotor hub about the bearing focus from a neutral position.

A rotor mounting assembly for a vertical take-off and landing aircraft includes a boom configured for mounting to a wing of the aircraft; a mount for mounting a rotor assembly, the mount connected to the boom at a joint and tiltable about the joint from a forward thrust orientation in which the rotor assembly can provide forward thrust for forward flight to a vertical thrust orientation in which the rotor assembly can provide vertical thrust for vertical take-off and landing and hover; a multi-link assembly extending from the boom to the mount; and a rotary actuator for actuating the multi-link assembly to control tilting of the mount.

One embodiment is an aircraft including first and second fuselages; a wing assembly connecting the first and second fuselages, wherein the first and second fuselages are parallel to one another; first and second forward propulsion systems tiltably attached to forward ends of the first and second fuselages; and first and second aft propulsion systems fixedly attached proximate aft ends of the first and second fuselages.

In an aspect of the present disclosure is a computing device for predicting battery temperature in an electric aircraft, the computing device including a controller communicatively connected to the electric aircraft, the controller comprising: a battery model, the battery model configured to: receive a flight plan; instantiate a machine-learning model, wherein the machine-learning model is trained as a function of a training set correlating flight plan data to battery temperature labels.

In an aspect of the present disclosure is an electric aircraft lift motor with air cooling, the motor including a stator connected to the electric aircraft, the stator including: an inner cylindrical surface and an outer cylindrical surface, wherein each of the inner cylindrical surface and the outer cylindrical surface is coaxial about an axis of rotation; and a rotor coaxial within the stator, the rotor including a rotor cylindrical surface, wherein the rotor cylindrical surface and the inner cylindrical surface combine to form an air gap between the rotor cylindrical surface and the inner cylindrical surface; and a first fan connected to an axial end of the rotor and configured to rotate with the rotor, the first fan comprising at least a blade configured to direct air toward the air gap.

An aircraft with increased crash robustness including a fuselage with a forward end, an opposite rear end, a ventral surface, and a dorsal surface. The aircraft further including a longitudinal axis running from the rear end to the forward end and a dorsoventral axis orthogonal to the longitudinal axis and running from the dorsal surface to the ventral surface. The aircraft also including at least a battery module located within the fuselage comprising a plurality of battery cells, each battery cell includes an axial axis positioned orthogonally to each of the longitudinal axis and the dorsoventral axis, and each battery cell has a plurality of radial axes orthogonal to the axial axis, wherein the plurality of radial axes includes a first radial axis aligned with the longitudinal axis and a second radial axis aligned with the dorsoventral axis.

In an aspect, a system for propeller parking control for an electric aircraft. The system include at least a sensor and a computing device. A sensor may be configured to generate angular datum. The computing device may be configured to generate a trajectory command as a function of angular datum. The computing device may also be configured to initiate the transition from hover to fixed-wing flight as a function of a trajectory command.

A system and method for the remote piloting of an electric aircraft is illustrated. The system comprises a remote device located outside an electric aircraft, wherein the remote device is configured to receive a flight command input from a user and transmit the flight command input to a flight controller located on the aircraft. The flight controller is located inside the aircraft and configured to receive the flight command input from the remote device and enact the flight command autonomously as a function of the flight command input.

A system and method for the remote piloting of an electric aircraft is illustrated. The system comprises a remote device located outside an electric aircraft, wherein the remote device is configured to receive a flight command input from a user and transmit the flight command input to a flight controller located on the aircraft. The flight controller is located inside the aircraft and configured to receive the flight command input from the remote device and enact the flight command autonomously as a function of the flight command input.