The invention describes a Vacuum Shell Airfoil which includes: (1) a circular shell, and (2) multiple fins where each of the multiple fins includes a bottom, a top, a front, a back, a first side and a second side wherein at least a portion of the bottom of each of the multiple fins is attached to the circular shell. The Vacuum Shell Airfoil can also include: a stabilization ring positioned above the circular shell where at least a portion of at least two fins are attached to the stabilization ring, a stabilization ring that is positioned above the circular shell where at least a portion of each of the multiple fins is attached to the stabilization ring, multiple fins which are radially positioned along the circular shell, which may further include a cylindrical guard rail positioned around the Vacuum Shell Airfoil. The circular shell of the Vacuum Shell Airfoil may be constructed of carbon fiber and the multiple fins may also be constructed of carbon fibers. The Vacuum Shell Airfoil can be used to more efficiently produce the lift that is necessary to propel and suspend aircraft such as Vertical Take Off and Land (VTOL) aerospace vehicles.

A flying apparatus includes a main structure and a rotative wing surface, the rotation of the wing surface allowing stabilizing the apparatus (100). A fuselage hangs from the wing surface around a hanging point, allowing the wing surface and the fuselage be moveable independently with respect to each other and the wing surface is configured as a disc to manoeuvre the apparatus and including one or more elements acting as security and secondary command and control surfaces, orienting the apparatus in desired directions. The main structure and wing surface can overwrap at least partially the the fuselage in order to improve the aerodynamic performance. The airframe or fuselage and the wing surface are rotatable around any of three rotational axes independently.

An aircraft impeller (001) and an aircraft, relating to the field of aircraft drive components, the aircraft impeller (001) including a frame body (100) and a rotating wheel part (200); the frame body (100) includes a mounting groove (130), the rotating wheel part (200) being fixedly arranged in the mounting groove (130); the mounting groove (130) has an axial centre line (105); the mounting groove (130) also has an open face and a bottom face (131) arranged opposite to one another; the rotating wheel part (200) includes at least one vane (210) distributed around the axial centre line (105), the vane (210) including a windward face (211); at the connecting point of the windward face (211) and the open face, the angle of the tangent plane of the windward face (211) and the open face is an acute angle.

A tension airfoil assembly includes an outer rim located concentrically with a hub supported by a plurality of spokes, each spoke extending therebetween. A series of airfoils, each airfoil having an aerodynamically lifting shape extending between a leading edge and a trailing edge. Each airfoil of the series of airfoils is assembled to the tension airfoil assembly by coupling an area of the airfoil proximate the leading edge to a leading edge spoke and an area of the airfoil proximate the trailing edge to a trailing edge spoke. The airfoils are arranged having a gap provided between the trailing edge of each forward located airfoil and the leading edge of each trailing located airfoil. The tension airfoil assembly can be employed as a propulsion and/or lifting device integrated into a vehicle, such as an airplane, a helicopter, a tandem rotor helicopter, etc.

A multirotor aircraft that is adapted for vertical take-off and landing. The multirotor aircraft comprises a fuselage, a tail boom that is provided with a vertical fin, a thrust producing units assembly that is provided for producing thrust in operation, at least one lower wing which comprises a lower wing inboard section that is connected to the fuselage and a lower wing outboard section that forms a lower wing tip, and at least one upper wing which is connected to the vertical fin and which forms an upper wing tip. The at least one upper wing is joined to the at least one lower wing in a joined-wing configuration.

A flying apparatus includes a main structure and a rotative wing surface, the rotation of the wing surface allowing stabilizing the apparatus (100). A fuselage hangs from the wing surface around a hanging point, allowing the wing surface and the fuselage be moveable independently with respect to each other and the wing surface is configured as a disc to manoeuvre the apparatus and including one or more elements acting as security and secondary command and control surfaces, orienting the apparatus in desired directions. The main structure and wing surface can overwrap at least partially the the fuselage in order to improve the aerodynamic performance.

The airframe or fuselage and the wing surface are rotatable around any of three rotational axes independently.

An aircraft impeller (001) and an aircraft, relating to the field of aircraft drive components, the aircraft impeller (001) including a frame body (100) and a rotating wheel part (200); the frame body (100) includes a mounting groove (130), the rotating wheel part (200) being fixedly arranged in the mounting groove (130); the mounting groove (130) has an axial centre line (105); the mounting groove (130) also has an open face and a bottom face (131) arranged opposite to one another; the rotating wheel part (200) includes at least one vane (210) distributed around the axial centre line (105), the vane (210) including a windward face (211); at the connecting point of the windward face (211) and the open face, the angle of the tangent plane of the windward face (211) and the open face is an acute angle.

A multirotor aircraft that is adapted for vertical take-off and landing. The multirotor aircraft comprises a fuselage, a tail boom that is provided with a vertical fin, a thrust producing units assembly that is provided for producing thrust in operation, at least one lower wing which comprises a lower wing inboard section that is connected to the fuselage and a lower wing outboard section that forms a lower wing tip, and at least one upper wing which is connected to the vertical fin and which forms an upper wing tip. The at least one upper wing is joined to the at least one lower wing in a joined-wing configuration.

The present invention discloses a low-noise novel thruster, in which a rotor casing is located at an air inlet side of a stator casing, at an inner middle portion of the rotor casing a rotor core is provided which is driven to rotate by a driving module; a rotor core is provided at in inner middle portion of the stator casing; the rotor casing is of a streamlined cylindrical structure with unequal diameter, and the main body of the rotor blade is parallel with the axial direction, and provided with a smooth curve in the rotating direction of the blade adjacent to an edge portion of an air inlet side. The present application provides a new thruster, which has same energy consumption and safety as propellers, but at a significantly greater thrust than the propeller, the more significant the advantage is at higher speeds.

A rotating circular aerofoil system that includes a disc body that has an aerofoil shape in cross section. The aerofoil shape has an angle of attack that is symmetrical. The disc body's includes a circular inner edge which forms a circular center opening and the disc body's leading edge. The disc body also includes an outer edge that forms the trailing edge. Intersecting ribs extend across the center opening and include a shaft opening that attaches to a rotating shaft. Formed on the top and bottom surfaces of the disc body are evenly spaced apart, extending T-shaped or L-shaped fins. In one embodiment, an air blower or impeller is attached to a hollow shaft linked to an air pump. When the air pump is activated, air is delivered to the air blower and impeller that distributes the air over the top surface of the disc body to improve lift.