Abstract: In an aspect the present disclosure is directed to an electric aircraft. An electric aircraft may include a plurality of fixed wings, a tail, a first boom, and a second boom and a plurality of lift components. The aircraft also includes a tail affixed to the aft end of the fuselage, a first boom including a first rear end affixed to the tail and a first forward end proximal to the fore end of the fuselage, wherein the first boom is affixed to a first wing, a second boom including a second rear end affixed to the tail and a second forward end proximal to the fore end of the fuselage, wherein the second boom is affixed to the second wing. The aircraft may include a plurality of lift components which may be affixed to the booms.

Abstract: In an aspect the present disclosure is directed to an electric aircraft. An electric aircraft may include a plurality of fixed wings, a tail, a first boom, and a second boom and a plurality of lift components. The aircraft also includes a tail affixed to the aft end of the fuselage, a first boom including a first rear end affixed to the tail and a first forward end proximal to the fore end of the fuselage, wherein the first boom is affixed to a first wing, a second boom including a second rear end affixed to the tail and a second forward end proximal to the fore end of the fuselage, wherein the second boom is affixed to the second wing. The aircraft may include a plurality of lift components which may be affixed to the booms.

Abstract: A hybrid electric vertical takeoff and landing (VTOL) aircraft. The hybrid electric VTOL aircraft generally includes a fuselage, a pair of wings, a pair of booms, a plurality of flight components and a power system. The wings are connected to the fuselage and extend generally laterally therefrom with each wing on either side of the fuselage. Each boom is connected to a respective one of the wings and extends generally longitudinally and parallel to the fuselage. The plurality of flight components is configured to provide thrust to the hybrid electric VTOL aircraft. The power system is configured to power the plurality of flight components and includes at least a fuel tank and a generator, and at least a battery. The at least a fuel tank is mounted to at least one of the booms. The at least a battery configured to power the plurality of flight components.

Abstract: A rotor for a motor of an electric aircraft is provided. The rotor may include a hub, which includes a plurality of magnets fixed to an inner surface of the hub that are configured to interact with a stator of the motor to rotate rotor. The rotor also includes redial spokes that extend from the hub and provide structural support to the rotor. The rotor may also include a hoop, which provides balance for rotor during operation of motor and may include an integrated fan that provides cooling to various components of the motor.

Abstract: A system for rolling landing gear is illustrated. System includes a skid component attached to an aircraft and comprising at least a skid tube oriented laterally to a longitudinal axis of the aircraft. System also includes at least a wheel journaled on a rotational fulcrum and at least a biasing means attaching the rotational fulcrum to the skid tube, wherein the biasing means comprises at least a leaf spring and exerts a recoil force resisting upward displacement of the rotational fulcrum with respect to the skid tube.

Abstract: A fuel pod for a hybrid electric aircraft. The fuel pod includes a housing, a fuel tank, a generator and a connection mechanism. The fuel tank is contained within the housing and is configured to hold a fuel therein. The generator is contained within the housing and is connected to the fuel tank. The generator is configured to power at least one of a plurality of flight components of a hybrid electric aircraft. The connection mechanism is at the housing and is configured to removably attach the fuel pod to the hybrid electric aircraft. The connection mechanism includes an electrical interface configured to electrically link to at least one of the plurality of flight components of the hybrid electric aircraft, and a communication interface configured to communicatively link to a flight controller communicatively connected to the hybrid electric aircraft.

Abstract: A selectively deployable heated propulsor system which may be integrated into vehicles, airplanes, or any other machinery configured for flight. The system includes a structural feature that includes a mounted propulsor including a rotor and a motor mechanically coupled to the rotor allowing the rotor to rotate when in an activated mode. The mounted propulsor includes a chamber configured to support a first configuration where the propulsor and the rotor are stowed and heated in an enclosed environment, and a second configuration where the rotor is deployed.

Abstract: In an aspect the current disclosure is directed to an electric aircraft, wherein the electric aircraft is comprised of a plurality of flight components and a flight controller. A plurality of flight components is comprised of a plurality of control surfaces, a plurality of lift propulsors, at least a thrust propulsor, and a plurality of electric motors configured to power the plurality of propulsors. The flight controller is communicatively connected to a pilot input and flight components. The flight controller is configured to receive control datum from a pilot input and generate an output datum as a function of the control datum.

Abstract: A system for in-flight stabilization including a plurality if flight components mechanically coupled to an aircraft. The system further comprises a sensor mechanically coupled to the aircraft, wherein the sensor is configured to detect a failure datum of the flight component. The system comprises a vehicle controller communicatively connected to the sensor and is configured to receive the failure datum of a flight component of the aircraft from the sensor, generate a mitigating response to be performed by at least a flight component of the plurality of flight components, and initiate the at least a flight component of the plurality of flight components. Initiating the flight component of the plurality of flight components further includes performing the mitigating response.

Abstract: In an aspect, a system for fixed-pitch lift configured for use in an electric aircraft includes a plurality of flight components mechanically coupled thereto, each configured to provide lift to the electric aircraft. The electric aircraft also includes a first pusher mechanically coupled to a first owing of the electric aircraft, wherein the first pusher is configured to provide forward flight to the electric aircraft, a second pusher mechanically coupled to a second wing of the electric aircraft, wherein the second pusher is configured to provide forward flight to the electric aircraft as well, a sensor that is configured to detect vertical lift and forward flight from a pilot control and generate a command datum, as a function of the pilot control, a flight controller which may include a computing device configured to receive the command datum and direct the electric aircraft, as a function of the command datum.

Abstract: A system for rolling landing gear is illustrated. System includes a skid component attached to an aircraft and comprising at least a skid tube oriented laterally to a longitudinal axis of the aircraft. System also includes at least a wheel journaled on a rotational fulcrum and at least a biasing means attaching the rotational fulcrum to the skid tube, wherein the biasing means comprises at least a leaf spring and exerts a recoil force resisting upward displacement of the rotational fulcrum with respect to the skid tube.

Abstract: In an aspect a system for charging from an electric vehicle charger to an electric grid, the system comprising an electric grid, wherein the electric grid is configured to trickle charge the electric vehicle recharging component, an electric vehicle recharging component connected to at least the electric grid, the electric vehicle recharging component comprising, at least a battery storage system, a power delivery station configured to deliver power to an energy source of an electric vehicle, and a computer device, the computer device configured to detect a failure of the electric grid, and power the electric grid in an event of the failure.

Abstract: In an aspect a system for loading and securing a payload in an electrical vertical take-off and landing (eVTOL) aircraft may comprise a fuselage further comprising structural elements configured to provide physical support for the aircraft fuselage. An eVTOL aircraft may also comprise a swing nose, where a portion of the nose of the aircraft may swing on a hinge in a radial direction orthogonal to the longitudinal axis of the aircraft. The hinge may be coupled to at least a portion of the fuselage and at least a portion of the nose of the aircraft. A latching mechanism may be configured to secure a payload in an aircraft fuselage. A conveyor mechanism may be configured to transport a payload into the fuselage from the opening of the aircraft.

Abstract: A system for maintaining attitude control under degraded or depleted energy source conditions using multiple electric propulsors includes a plurality of propulsors, at least an energy source providing electric power to the plurality of propulsors and a vehicle controller communicatively coupled to each propulsor and configured to calculate initial power levels for the plurality of propulsors, the initial power levels including an initial power level for each propulsor, determine an energy output capacity of the least an energy source under load, calculate, by the vehicle controller, an aggregate potential demand of the plurality of propulsors as a function of the initial power levels, determine that electric potential is insufficient to match the aggregate potential demand, and for each initial power level generate a reduced power level, the reduced power level less than the initial power level and direct a corresponding propulsor to consume electrical power at the reduced power level.

Abstract: A system for rolling landing gear includes a skid component attached to an aircraft, wherein the skid component further comprises a first skid tube oriented laterally to a longitudinal axis of the axis, a second skid tube oriented laterally to the longitudinal axis of the aircraft, wherein the second skid tube is parallel to the first skid tube, a first wheel journaled on a first rotational fulcrum, a second wheel journaled on a second rotational fulcrum, a first biasing means attaching the first rotational fulcrum to the first skid tube, and a second biasing means attaching the second rotational fulcrum to the second skid tube, wherein the first biasing means and second biasing means exert a recoil force resisting upward displacement of the first rotational fulcrum and second rotational fulcrum with respect to the first skid tube and second skid tube.

Abstract: A selectively deployable heated propulsor system which may be integrated into vehicles, airplanes, or any other machinery configured for flight. The system includes a structural feature that includes a mounted propulsor including a rotor and a motor mechanically coupled to the rotor allowing the rotor to rotate when in an activated mode. The mounted propulsor includes a chamber configured to support a first configuration where the propulsor and the rotor are stowed and heated in an enclosed environment, and a second configuration where the rotor is deployed.

Abstract: A system for in-flight stabilization including a plurality if flight components mechanically coupled to an aircraft. The system further comprises a sensor mechanically coupled to the aircraft, wherein the sensor is configured to detect a failure datum of the flight component. The system comprises a vehicle controller communicatively connected to the sensor and is configured to receive the failure datum of a flight component of the aircraft from the sensor, generate a mitigating response to be performed by at least a flight component of the plurality of flight components, and initiate the at least a flight component of the plurality of flight components. Initiating the flight component of the plurality of flight components further includes performing the mitigating response.

Abstract: A system for maintaining attitude control under degraded or depleted energy source conditions using multiple electric propulsors includes a plurality of propulsors, at least an energy source providing electric power to the plurality of propulsors and a vehicle controller communicatively coupled to each propulsor and configured to calculate initial power levels for the plurality of propulsors, the initial power levels including an initial power level for each propulsor, determine an energy output capacity of the least an energy source under load, calculate, by the vehicle controller, an aggregate potential demand of the plurality of propulsors as a function of the initial power levels, determine that electric potential is insufficient to match the aggregate potential demand, and for each initial power level generate a reduced power level, the reduced power level less than the initial power level and direct a corresponding propulsor to consume electrical power at the reduced power level.

Abstract: A selectively deployable heated propulsor system which may be integrated into vehicles, airplanes, or any other machinery configured for flight. The system includes a structural feature that includes a mounted propulsor including a rotor and a motor mechanically coupled to the rotor allowing the rotor to rotate when in an activated mode. The mounted propulsor includes a chamber configured to support a first configuration where the propulsor and the rotor are stowed and heated in an enclosed environment, and a second configuration where the rotor is deployed.

Abstract: A system for in-flight stabilization including a plurality if flight components mechanically coupled to an aircraft. The system further comprises a sensor mechanically coupled to the aircraft, wherein the sensor is configured to detect a failure datum of the flight component. The system comprises a vehicle controller communicatively connected to the sensor and is configured to receive the failure datum of a flight component of the aircraft from the sensor, generate a mitigating response to be performed by at least a flight component of the plurality of flight components, and initiate the at least a flight component of the plurality of flight components. Initiating the flight component of the plurality of flight components further includes performing the mitigating response.