A vertical takeoff and landing aerial vehicle and a cooling system for the aerial vehicle. Heat dissipation in an arm of an aerial vehicle is achieved by installing a fan in a hollow interior of each of a left linear support and a right linear support of the aerial vehicle, thereby achieving the purposes of lowering temperature in the arm and protecting equipment in the arm.

Aspects relate to a charger for an electric aircraft with failure monitoring and method for its use. An exemplary charger for an electric aircraft with failure monitoring includes a charging circuit. Included within the charging circuit is a connector configured to mate with an electric aircraft port of an electric aircraft and at least a current conductor configured to conduct a current. At least a conductor comprises a direct current conductor configured to conduct a direct current; and an alternating current conductor configured to conduct an alternating current. A charger may include a control circuit configured to command the charging circuit of an electric aircraft as a function of charging datum. A charger may also include a failure monitor circuit, the failure monitor circuit configured to: detect a failure and initiate a failure mitigation procedure as a function of failure detection.

To provide an aerial vehicle that can realize ease of operation during driving. An aerial vehicle according to the present technology includes: a vehicle body extending in a front-rear direction; a saddle section provided on an upper side of the vehicle body; a grip section provided on the front side of the saddle section in the vehicle body; and a rotary wing section which is provided in the vehicle body and which generates lift and/or thrust with respect to the vehicle body; wherein an operation section for performing operations pertaining to actions relating to ascent and/or propulsion of the vehicle body is provided in the grip section.

An aircraft comprising two half-wings extending to either side of an airframe. The aircraft comprises at least one propeller arranged in the rear part of the airframe. The aircraft comprises a rotary wing provided with two synchronized counter-rotating rotors carried respectively by the half-wings. The aircraft comprises a power plant comprising at least one engine and a mechanical interconnection system connecting the power plant permanently to the rotors except in the event of failure and during training, and to the at least one propeller.

Vertical take-off, landing and horizontal straight flight of an aircraft includes activation a plurality of front and rear lifting in-ring propellers, each of which is connected to a respective independently operating electric motor. In addition, horizontal straight flight of the aircraft includes activation of additional left and right pushing propellers, each of which is connected to an independently operating electric motor. The front and rear lifting in-ring propellers are respectively positioned generally horizontally and symmetrically opposite to one another and equidistantly relative to a longitudinal axis of the aircraft. The right pushing propeller and the left pushing propeller are positioned generally vertically and symmetrically opposite to one another and equidistantly relative to the longitudinal axis of the aircraft.

Vertical take-off, landing and horizontal straight flight of an aircraft includes activation a plurality of front and rear lifting propellers, each of which is connected to a respective independently operating electric motor. In addition, horizontal straight flight of the aircraft includes activation of additional left and right pushing propellers, each of which is connected to an independently operating electric motor. The front and rear lifting propellers are respectively positioned generally horizontally and symmetrically opposite to one another and equidistantly relative to a longitudinal axis of the aircraft. The right pushing propeller and the left pushing propeller are positioned generally vertically and symmetrically opposite to one another and equidistantly relative to the longitudinal axis of the aircraft.

Vertical take-off, landing and horizontal straight flight of an aircraft includes activation a plurality of front and rear lifting in-ring propellers, each of which is connected to a respective independently operating electric motor. In addition, horizontal straight flight of the aircraft includes activation of additional left and right pushing in-ring propellers, each of which is connected to an independently operating electric motor. The front and rear lifting in-ring propellers are respectively positioned generally horizontally and symmetrically opposite to one another and equidistantly relative to a longitudinal axis of the aircraft. The right pushing in-ring propeller and the left pushing in-ring propeller are positioned generally vertically and symmetrically opposite to one another and equidistantly relative to the longitudinal axis of the aircraft.

An electric vertical takeoff and landing (EVTOL) aircraft is disclosed. In some aspects, the aircraft comprises a main wing, an empennage, two lift propulsors, and two lift/thrust propulsors each mounted on a tilt axis.

An aircraft includes a first battery, provisions for transport that are powered by a second battery, and a management system for transferring energy between the first battery and the second battery.

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.