Deployment system for adjusting a leading edge high-lift device, in particular a slat, between a retracted position, in which, in use, the high-lift device is retracted with respect to an airfoil, and at least one deployed position, in which, in use, the high-lift device is deployed with respect to the airfoil, comprising at least one actuation unit that is configured to actuate the high-lift device between the retracted position and the at least one deployed position, at least one guidance unit that is configured to guide the high-lift device during adjustment between the retracted position and the at least one deployed position along an adjustment path, wherein the guidance unit is independent from the actuation unit.

An aircraft includes a fuselage and a pair of wings. Each wing is coupled to the fuselage at a wing-fuselage joint, and is supported by a strut coupled to the fuselage at a strut-fuselage joint and coupled to the wing at a strut-wing joint. The strut-fuselage joint is located below and at least partially aft of the wing-fuselage joint. The wing generates a lifting force when air passes over the wing. The lifting force induces a vertical moment about the wing-fuselage joint due to the location of the strut-fuselage joint below and at least partially aft of the wing-fuselage joint. The wing and/or the strut has a structural arrangement configured to counteract the vertical moment.

An aircraft includes a fuselage and a pair of wings. Each wing is coupled to the fuselage at a wing-fuselage joint, and is supported by a strut coupled to the fuselage at a strut-fuselage joint and coupled to the wing at a strut-wing joint. The strut-fuselage joint is located below and at least partially aft of the wing-fuselage joint. The wing generates a lifting force when air passes over the wing. The lifting force induces a vertical moment about the wing-fuselage joint due to the location of the strut-fuselage joint below and at least partially aft of the wing-fuselage joint. The wing and/or the strut has a structural arrangement configured to counteract the vertical moment.

A VTOL (vertical take-off and landing) box-wing aerial vehicle with multirotor to provide VTOL flight includes a detachable cabin, centered fuselage, a pair of first wings extending outward from the upper portion of the fuselage and a pair of second wings extending outwardly and from the lower portion of the fuselage. The first and second wings are spaced apart longitudinally and vertically. The pylon joints the first wing and second wing at the tip to form the box-wing. The pylon includes heading control rudder. Secured to the wing or pylon or both wing and pylon, an overhead boom extending longitudinally to support a plurality of lift rotors or tiltable rotors for VTOL flight. Finally, the overhead boom mounted tiltable rotors propel the vehicle forward to generate lift from the wings. Furthermore, the wings are equipped with elevators and ailerons for flight control.

An aircraft is disclosed. The aircraft includes a first pair of wings, each wing in the first pair of wings including one or more actuating flaps configured to move to facilitate the aircraft transitioning between a forward cruise mode and a vertical hover mode, and operating in one of the forward cruise mode or the vertical hover mode. The aircraft further includes a second pair of wings, and one or more propellers coupled to the second pair of wings and oriented horizontally to provide upward lift.

An aircraft is disclosed. The aircraft includes a first pair of wings, each wing in the first pair of wings including one or more actuating flaps configured to move to facilitate the aircraft transitioning between a forward cruise mode and a vertical hover mode, and operating in one of the forward cruise mode or the vertical hover mode. The aircraft further includes a second pair of wings, and one or more propellers coupled to the second pair of wings and oriented horizontally to provide upward lift.

The present invention includes a distributed propulsion system for a craft that comprises a frame, a plurality of hydraulic or electric motors disposed within or attached to the frame in a distributed configuration; a propeller operably connected to each of the hydraulic or electric motors, a source of hydraulic or electric power disposed within or attached to the frame and coupled to each of the disposed within or attached to the frame, wherein the source of hydraulic or electric power provides sufficient energy density for the craft to attain and maintain operations of the craft, a controller coupled to each of the hydraulic or electric motors, and one or more processors communicably coupled to each controller that control an operation and speed of the plurality of hydraulic or electric motors.

The present invention includes a distributed propulsion system for a craft that comprises a frame, a plurality of hydraulic or electric motors disposed within or attached to the frame in a distributed configuration; a propeller operably connected to each of the hydraulic or electric motors, a source of hydraulic or electric power disposed within or attached to the frame and coupled to each of the disposed within or attached to the frame, wherein the source of hydraulic or electric power provides sufficient energy density for the craft to attain and maintain operations of the craft, a controller coupled to each of the hydraulic or electric motors, and one or more processors communicably coupled to each controller that control an operation and speed of the plurality of hydraulic or electric motors.

An aircraft includes a closed wing, a fuselage at least partially disposed within a perimeter of the closed wing, and one or more spokes coupling the closed wing to the fuselage. A source of electric power is disposed within or attached to the closed wing, fuselage or one or more spokes. A plurality of electric motors are disposed within or attached to the one or more spokes in a distributed configuration. Each electric motor is connected to the source of electric power. A propeller is operably connected to each of the electric motors and proximate to a leading edge of the one or more spokes. One or more processors are communicably coupled to the plurality of electric motors. A longitudinal axis of the fuselage is substantially vertical in vertical takeoff and landing and stationary flight, and substantially in a direction of a forward flight in a forward flight mode.

An aircraft includes a closed wing, a fuselage at least partially disposed within a perimeter of the closed wing, and one or more spokes coupling the closed wing to the fuselage. A source of electric power is disposed within or attached to the closed wing, fuselage or one or more spokes. A plurality of electric motors are disposed within or attached to the one or more spokes in a distributed configuration. Each electric motor is connected to the source of electric power. A propeller is operably connected to each of the electric motors and proximate to a leading edge of the one or more spokes. One or more processors are communicably coupled to the plurality of electric motors. A longitudinal axis of the fuselage is substantially vertical in vertical takeoff and landing and stationary flight, and substantially in a direction of a forward flight in a forward flight mode.