A vertical takeoff and landing (VTOL) aircraft, configured to transport passengers and/or cargo, uses propellers during vertical flight and wings during forward flight to generate lift. The VTOL aircraft includes a front wing and a rear wing connected by inboard booms. The rear wing may include a wingtip boom attached to each free end of the wing. A propeller may be attached to each inboard boom and each wingtip boom. The propellers attached to the inboard booms may be stacked propellers including at least two co-rotating propellers. The aircraft can also include a cruise propeller attached to the tail region of the fuselage, where the cruise propeller is configured to rotate in a plane approximately perpendicular to the fuselage to generate thrust during forward flight.

A vertical takeoff and landing (VTOL) aircraft, configured to transport passengers and/or cargo, uses propellers during vertical flight and wings during forward flight to generate lift. The VTOL aircraft includes a front wing and a rear wing connected by inboard booms. The rear wing may include a wingtip boom attached to each free end of the wing. A propeller may be attached to each inboard boom and each wingtip boom. The propellers attached to the inboard booms may be stacked propellers including at least two co-rotating propellers. The aircraft can also include a cruise propeller attached to the tail region of the fuselage, where the cruise propeller is configured to rotate in a plane approximately perpendicular to the fuselage to generate thrust during forward flight.

An aircraft defining a longitudinal centerline and extending between a forward end and an aft end is provided. The aircraft includes a fuselage extending longitudinally between the forward end of the aircraft and the aft end of the aircraft; a primary wing assembly extending laterally outwardly with respect to the longitudinal centerline from a portion of the fuselage; a first engine mounted to the primary wing assembly; and a first engine wing assembly extending outward from the first engine.

An aircraft defining a longitudinal centerline and extending between a forward end and an aft end is provided. The aircraft includes a fuselage extending longitudinally between the forward end of the aircraft and the aft end of the aircraft; a primary wing assembly extending laterally outwardly with respect to the longitudinal centerline from a portion of the fuselage; a first engine mounted to the primary wing assembly; and a first engine wing assembly extending outward from the first engine.

Methods, systems, and apparatuses for an electric aircraft may be shown and described. The electric aircraft may include a body; a first wing and a second wing, each of the first wing and the second wing having a plurality of stabilizers and a plurality of flaps; a cockpit; and at least one of a dielectric elastomer power generator, a wind turbine, an electric jet turbine, and a rotational electromagnetic power generator mounted on a central plane surface on the body.

Methods, systems, and apparatuses for an electric aircraft may be shown and described. The electric aircraft may include a body; a first wing and a second wing, each of the first wing and the second wing having a plurality of stabilizers and a plurality of flaps; a cockpit; and at least one of a dielectric elastomer power generator, a wind turbine, an electric jet turbine, and a rotational electromagnetic power generator mounted on a central plane surface on the body.

A mounting assembly for coupling an accessory to a frame including a base configured to be coupled to the frame; the base having a hollow portion; the hollow portion including a receiving end including a tapered socket; an internal interlocking portion adjacent to the tapered socket; and a securing end opposite from the receiving end; a shaft configured to be connected to an accessory at a first end and received in the hollow portion of the base in an engaged position, the shaft including a tapered boss adjacent to the first end, the tapered boss configured to engage the tapered socket; an external interlocking portion adjacent to the tapered boss configured to engage the internal interlocking portion; and a second end opposite from the first end, the second end including a threaded surface; wherein when the shaft is in an engaged position, the shaft is static in the hollow portion.

The invention relates to a wing for an airplane having at least two winglets, wherein a local angle of attack at the upstream winglet shall be reduced by a passive elastic morphing in heavy load conditions and wherein stall shall occur for the downstream winglet, then. Both serves for limiting and reducing the forces and torques produced by the winglets.

The invention relates to a wing for an airplane having at least two winglets, wherein a local angle of attack at the upstream winglet shall be reduced by a passive elastic morphing in heavy load conditions and wherein stall shall occur for the downstream winglet, then. Both serves for limiting and reducing the forces and torques produced by the winglets.