A skin for an aircraft is configured to be disposed on a first rigid member and on a second rigid member. The second rigid member is movable with respect to the first rigid member and a distance is defined between the first rigid member and the second rigid member. A morphing member of the skin extends between the first rigid member and the second rigid member. The morphing member comprises first segments forming a first portion attached to the first rigid member and second segments forming a second portion attached to the second rigid member. The first and second portions are separated along a substantially linear seam in the absence of change in the distance and an orientation between the first rigid member and the second rigid member.

A skin for an aircraft is configured to be disposed on a first rigid member and on a second rigid member. The second rigid member is movable with respect to the first rigid member and a distance is defined between the first rigid member and the second rigid member. A morphing member of the skin extends between the first rigid member and the second rigid member. The morphing member comprises first segments forming a first portion attached to the first rigid member and second segments forming a second portion attached to the second rigid member. The first and second portions are separated along a substantially linear seam in the absence of change in the distance and an orientation between the first rigid member and the second rigid member.

A method of manufacturing a foldable aerodynamic structure, such as a wing, for an aircraft. The wing (1) including an inner region (1) and an outer region (3) rotatable relative to the inner region between a flight configuration and a ground configuration. The method includes designing the foldable aerodynamic structure by determining the location and orientation of an Euler axis of rotation (11) about which the outer region rotates to achieve the ground configuration and determining a cut plane (13), perpendicular to that Euler axis, separating the inner and outer regions; and iteratively repeating this process until a preferred cut plane (13) is obtained that satisfies at least one design criteria.

A method of manufacturing a foldable aerodynamic structure, such as a wing, for an aircraft. The wing (1) including an inner region (1) and an outer region (3) rotatable relative to the inner region between a flight configuration and a ground configuration. The method includes designing the foldable aerodynamic structure by determining the location and orientation of an Euler axis of rotation (11) about which the outer region rotates to achieve the ground configuration and determining a cut plane (13), perpendicular to that Euler axis, separating the inner and outer regions; and iteratively repeating this process until a preferred cut plane (13) is obtained that satisfies at least one design criteria.

An aircraft wing comprises a fixed wing, and a wing tip device at the tip thereof. The wing tip device is configurable between (i) a flight configuration for use during flight, and (ii) a ground configuration for use during ground based operations. In the ground configuration with span of the wing is reduced. The wing further comprises a locking mechanism including a locking pin with a longitudinal axis, the locking pin associated with one of the fixed wing and the wing tip device, and a bush associated with the other of the fixed wing and wing tip device, the bush configured to receive the locking pin. The bush is located within a bush housing arranged to allow relative movement of the bush in the direction of the longitudinal axis of the locking pin when the locking pin is received within the bush.

A flying vehicle with a flight part connected to a plurality of rotor wing parts and a main wing, wherein the main wing is configured such that the lift produced by the main wing during landing is reduced compared to the lift produced by the main wing during cruising. Furthermore, the main wing is fixed at a forward tilt with respect to the flight part. Furthermore, the rotor wing is connected at an angle that produces propulsion and lift during cruise. Furthermore, the rotor blades are connected at an angle that generates propulsive force during cruise.

A flying vehicle with a flight part connected to a plurality of rotor wing parts and a main wing, wherein the main wing is configured such that the lift produced by the main wing during landing is reduced compared to the lift produced by the main wing during cruising. Furthermore, the main wing is fixed at a forward tilt with respect to the flight part. Furthermore, the rotor wing is connected at an angle that produces propulsion and lift during cruise. Furthermore, the rotor blades are connected at an angle that generates propulsive force during cruise.

Airframes configured for stable in-flight transition between forward flight and vertical takeoff and landing are described herein. In one embodiment, an aircraft can include a fuselage, opposed wings extending from opposed sides of the fuselage, and a plurality of engines. At least one engine can be mounted to each of the opposed wings and at least a portion of each opposed wing including at least one of the plurality of engines can rotate relative to the fuselage around a rotation axis that is non-perpendicular and transverse to a longitudinal axis of the fuselage. Rotating portions of the wings including at least one of the plurality of engines in the described manner can provide a stable and smooth transition between vertical and forward flight.

Airframes configured for stable in-flight transition between forward flight and vertical takeoff and landing are described herein. In one embodiment, an aircraft can include a fuselage, opposed wings extending from opposed sides of the fuselage, and a plurality of engines. At least one engine can be mounted to each of the opposed wings and at least a portion of each opposed wing including at least one of the plurality of engines can rotate relative to the fuselage around a rotation axis that is non-perpendicular and transverse to a longitudinal axis of the fuselage. Rotating portions of the wings including at least one of the plurality of engines in the described manner can provide a stable and smooth transition between vertical and forward flight.

A folding wing hinge for a wing having a fixed wing portion and a folding wing portion, the folding wing hinge including a hinge pin including a hinge pin spline and having a first longitudinal axis, an input fitting coupled to one of the fixed wing portion and the folding wing portion, the input fitting including an input fitting spline and a second longitudinal axis, and a spline coupling member having a coupling spline configured to couple with the hinge pin spline and the input fitting spline so that the first longitudinal axis moves relative to the second longitudinal axis by a first predetermined amount of movement.