An aerial vehicle adapted for vertical takeoff and landing using mounted thrust producing elements. An aerial vehicle which is adapted to vertical takeoff with the forward rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle uses one or more thrust producing elements on both of the right and the left sides. The aerial vehicle may have one or more front thrust producing elements and one or more rear thrust producing elements on both of the right and the left sides of a main vehicle body.

A UAV with vertical takeoff and landing (VTOL) function having a plurality of lift propellers; a cabin engaged with a plurality of lift propellers; a water propulsion system engaged with the cabin to push the cabin in a forward direction when the cabin is at least partially immersed in water; at least one water inlet engaged with the water propulsion system; the cabin is a cargo hold or a passenger cabin. The UAV provided by the disclosure can realize vertical takeoff and landing in the water area, and fly, drive and navigate freely in the whole area.

A VTOL aircraft (1) having a fuselage (2) for transporting passengers and/or load, front and rear wings (3, 4) attached to the fuselage, a right connecting beam (5a) and a left connecting beam (5b), which connecting beams structurally connect the front wing and the rear wing, and which connecting beams are spaced apart from the fuselage, and at least two lifting units (M1-M6) on each one of the connecting beams. The lifting units each include at least one propeller (6b) and at least one motor (6a) driving the propeller, preferably an electric motor, and are arranged with their respective propeller axis in an essentially vertical orientation. The front wing, at least in portions thereof, has a sweep angle γ between γ=450 and γ=135°, and the rear wing, at least in portions thereof, has a forward sweep with sweep angle β≥30°.

An aerial vehicle of a box wing design adapted for vertical takeoff and landing using mounted thrust producing elements. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle uses one or more thrust producing elements on both of the right and the left sides. The aerial vehicle may have one or more front thrust producing elements and one or more rear thrust producing elements on both of the right and the left sides of a main vehicle body.

A lift rotor arrangement (100) for a VTOL aircraft (200). The lift rotor arrangement (100) comprises: a fairing (6) mounted on a wing segment (10); and first and second rotor blades (17, 18) mounted on a first shaft (4) extending vertically from the fairing (6). The first shaft (4) is movable between an extended position in which the first and second rotor blades (17, 18) are vertically spaced above the wing segment (10) and are rotatable to provide vertical lift, and a retracted position in which the first and second rotor blades (17, 18) are rotationally-fixed with the first rotor blade (17) stowed within the wing segment (10). The blades (17, 18) may be rotatable around an axis substantially perpendicular to the axis of the respective first shaft (4) so as to act as ailerons/elevons in the retracted position.

Improved closed wing aircraft design and configuration with three wings on either side of the fuselage wherein at least one closed frame is established between the 1st wing (65) and the 2nd wing (67), by using at least one bracing entity. A separate closed frame is established between the 2nd wing (67) and the 3rd wing (71), by using at least one bracing entity. Each of said closed frames defines its own aerodynamic channel. The framework is strong and stiff, the mutually supported parts level out the stress, the load per wing is low. The fuselage is lifted in three points. It is possible to build a very large aircraft of composite materials. The Aspect Ratio is high and the wingspan is relatively short but there are embodiments wherein the 3rd wing has an extended folding tip section.

An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements and a set of tail mounted rotors for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle uses different configurations of its wing mounted rotors and propellers to reduce drag in all flight modes.

A vertical take-off and landing (VTOL) unmanned aerial vehicle having a foldable fixed wing and a twin-ducted fan power system (7) arranged at a tail portion of a fuselage in a transverse and tail propulsion arrangement provides lift for vertical take-off and landing and propulsion for horizontal flight. By means of deflection of a control servo plane arranged at a duct exit, a vectored thrust is provided to enable a fast attitude change. When the aerial vehicle takes off and lands vertically/flies at a low speed, the wing is folded to reduce the frontal area exposure to crosswind. When the aerial vehicle is flying horizontally, the wing is expanded to obtain larger lift. A Coanda effect is created at a trailing edge of the wing by suction of the duct to improve performance.

A vertical take-off and landing aircraft which uses fixed rotors for both VTOL and forward flight operations. The rotors form a synthetic wing and are positioned to achieve a high span efficiency. The rotors are positioned to even out the lift across the span of the synthetic wing. The synthetic wing may also have narrow front and rear airfoils which may provide structural support as well as providing lift during forward flight. The wing rotors are tilted forward and provide some forward propulsion during horizontal flight.

An aircraft (1) comprising a fuselage (4), an anhedral rearwardly-swept leading wing (5) for generating lift connected to an upper portion of the fuselage, and a dihedral forwardly-swept trailing wing (7) for generating lift attached to a lower portion of the fuselage. The trailing wing (7) is arranged to be vertically lower than the leading wing (5) in flight. The leading wing (5) and trailing wing (7) are blended together at their wingtips, forming a common wingtip (20), such that the underside surface (16) of the leading wing (5) forms a generally continuous and smoothly transitioning surface with the upper surface (22) of the trailing wing (7) so as to form a vortex guide surface (23) such that vortex air flow from the leading wing (5) is guided by the vortex guide surface (23) onto, or into the path of, the trailing wing (7).