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).

An actuator assembly for moving an aircraft wing tip device is disclosed. The wing tip device is rotatable about a hinge axis relative to a fixed wing of the aircraft. The hinge axis is orientated non-parallel to a line-of-flight direction of the aircraft. The actuator assembly includes a primary shaft having an axis of rotation orientated substantially parallel to the line-of-flight direction, a motor to cause rotation of the primary shaft, and a secondary shaft orientated substantially parallel to the hinge axis. The secondary shaft is couplable to the primary shaft and is arranged to rotate the wing tip device in response to the rotation of the primary shaft.

A monolithic skin for an aerodynamic structure is provided. The skin comprises a root end defining a root opening; a tip end opposite to the root end; a trailing-edge portion defining a slot opening extending from the root opening toward the tip end; a leading-edge portion extending spanwise from the root end to the tip end; and a middle portion extending between the trailing edge and the leading-edge portion and at least partially defining an open slot in fluid communication with the slot opening and root opening. The middle portion comprises an interior surface facing the open slot that is graded so that the middle portion decreases in thickness spanwise toward the root end. The middle portion also comprises a first integrated spar section extending from the interior surface to the tip end.

A monolithic skin for an aerodynamic structure is provided. The skin comprises a root end defining a root opening; a tip end opposite to the root end; a trailing-edge portion defining a slot opening extending from the root opening toward the tip end; a leading-edge portion extending spanwise from the root end to the tip end; and a middle portion extending between the trailing edge and the leading-edge portion and at least partially defining an open slot in fluid communication with the slot opening and root opening. The middle portion comprises an interior surface facing the open slot that is graded so that the middle portion decreases in thickness spanwise toward the root end. The middle portion also comprises a first integrated spar section extending from the interior surface to the tip end.

A propulsion and lift system for an aircraft includes a wing having an outboard end and a pylon assembly coupled to the outboard end of the wing. The propulsion and lift system also includes a wing extension rotatably coupled to the outboard end of the pylon assembly. The wing extension is rotatable between a flight position in a flight mode and a stow position in a storage mode. The wing extension folds inboard in the stow position, thereby reducing a wingspan of the aircraft in the storage mode.

Convertible-type aircraft, able to fly with the speed and the reduced operating costs of a fixed-wing aircraft and also to take-off/land vertically and hover/manoeuvre like an helicopter. The aircraft object of the invention comes in the form of a classical plane, with a fuselage (1), a fixed wing (2), an horizontal stabilizer (3) and a vertical fin (4), as well as one or several jet engines or turboprops (5) for propulsion and it comprises exposable rotors (6 and 7) installed inside the wing and possibly inside the horizontal stabilizer or the fuselage for lifting the aircraft for vertical take-off/landing and stationary flight. For the flight and the horizontal take-off/landing, the rotors are completely enclosed inside the wing and possibly inside the horizontal stabilizer or the fuselage.

A flap assembly for a fixed wing aircraft, comprising first and second flap portions, a compartments in the flap portions enclosing rechargeable batteries, motor controllers and electric motors, vertically-oriented slots in the first flap portion with propellers operable through a sidewall of the slot, such that the propeller in operation extends both over and under the top and bottom walls of the flap portion. With the flap assembly retracted in the wing the propeller is entirely enclosed in the length of the slot, and wherein the flap assembly is extended from the edge of the wing, enhancing area and curvature of the wing, increasing lift on the wing, exposing the slot, and with the slot exposed the motor is started spinning the propeller, providing increased airflow over the flap assembly, further increasing lift on the wing.

A flap assembly for a fixed wing aircraft, comprising first and second flap portions, a compartments in the flap portions enclosing rechargeable batteries, motor controllers and electric motors, vertically-oriented slots in the first flap portion with propellers operable through a sidewall of the slot, such that the propeller in operation extends both over and under the top and bottom walls of the flap portion. With the flap assembly retracted in the wing the propeller is entirely enclosed in the length of the slot, and wherein the flap assembly is extended from the edge of the wing, enhancing area and curvature of the wing, increasing lift on the wing, exposing the slot, and with the slot exposed the motor is started spinning the propeller, providing increased airflow over the flap assembly, further increasing lift on the wing.

A parasite aircraft for airborne deployment and retrieve includes a wing; a fuselage rotatably mounted to the wing; a dock disposed on top of the fuselage and configured to receive a maneuverable capture device of a carrier aircraft; a pair of tail members extending from the fuselage; and a plurality of landing gear mounted to the wing. A method of preparing a parasite aircraft for flight includes unfolding an end portion of a wing; unfolding an end portion of a tail member of the parasite aircraft; and rotating a fuselage of the parasite aircraft so that the fuselage is perpendicular to the wing. A method of preparing a parasite aircraft for storage includes rotating a fuselage of the parasite aircraft to be parallel with a wing of the parasite aircraft; folding an end portion of the wing; and folding an end portion of a tail member of the parasite aircraft.

An aircraft with wing tip devices, for example, folding wing tips, is disclosed. The folding wing tip may have a flight configuration for use during flight, and a ground configuration for use in ground-based operations. The ground configuration creates a shorter wing span than when the aircraft is in the flight configuration. A hinge arrangement protrudes beyond an outer surface of the fixed wing and wing tip device. In order to reduce the aerodynamic effect of the protruding hinge a fairing may be provided. In the flight configuration the fairing comprises a front portion blended into and extending rearwardly from the leading edge of the fixed wing and the wing tip device.