A wing for an aircraft including a main wing, slat, and connection assembly movable connecting the slat to the main wing and including an elongate slat track. A front end of the slat track is mounted to the slat. A rear end and an intermediate portion of the slat track are mounted to the main wing by a roller bearing that includes a guide rail mounted to the main wing and a first roller unit mounted to the rear end of the slat track and engaging the guide rail. The wing has redundant main load paths. The guide rail includes a guide rail primary structure engaging with the first roller unit and an additional reinforcement structure additionally reinforcing the guide rail primary structure in a lateral direction. The guide rail primary structure forms a first main load path. The reinforcement structure forms a redundant second main load path.

A flying vehicle comprising a wing ship body having a pair of wing spars secured thereto; and a plurality of hinged wing-rib assemblies disposed along each wing spar that allows the wings to be folded against the body of the flying vehicle. A method for folding or collapsing the wings of a wing-in-ground-effect wing ship comprising providing a wing-in-ground-effect wing ship having a pair of wings, and folding the wings toward and against the body of the wing-in-ground-effect wing ship. A fabric covered wing folding assembly including a pair of wings with each wing having a wing spar and covered by a fabric. A plurality of hinged wing-rib assemblies is disposed along each wing spar that allows the wings to be folded against the body of the aircraft. A method is provided for folding or collapsing the wings of an aircraft.

A wing having a wing box (20) defining a first wing profile with a first leading edge, a first trailing edge, a first top surface and a first bottom surface; a first appendage hinged on the wing box and defining a second wing profile, in turn comprising an end wall and a second trailing edge, a second top surface and a second bottom surface; the first appendage is movable between: a first position, in which the first and the second wing profiles are contiguous with each other and a second position, in which the second bottom surface and second top surface are respectively separated from the first bottom surface and first top surface; the wing box comprises a first spar having a curved section in a plane orthogonal to the associated first axis; the end wall is curved and arranged abutting against the first spar at least along the second top surface and the second bottom surface when the first movable appendage is in the first position.

A kit of parts for forming an aerofoil structure including a torsion box for use in attaching a fixed leading or trailing edge structure to the torsion box, and a fixed leading or trailing edge structure attachable to the torsion box. The torsion box includes a first mounting feature. The fixed leading or trailing edge structure includes a second mounting feature configured to engage with the first mounting feature. The first mounting feature and the second mounting feature are mutually configured to permit the first and second mounting features to be moved into engagement with each other along a first direction, and to prevent relative movement of the first and second mounting features along a second direction when the first and second mounting features are engaged with each other.

Disclosed is a wing in which, while a continuous surface is maintained, a chord length and camber of an airfoil may be modified via only a rotational drive alone, whereby a structure is simple and aerodynamic efficiency may be improved.

An aircraft wing has a flap arrangement with an inboard flap configured to move in a chordwise extension direction relative to the wing, the inboard flap having an outboard side, and an outboard flap adjacent to the inboard flap and configured to move in the chordwise extension direction relative to the wing, the outboard flap including an inboard side. A flap interconnect between the inboard flap and outboard flap has a roller mounted to a pin extending from the outboard side of the inboard flap and a guide track extending from the inboard side of the outboard flap. The guide track engages the roller on the inboard flap to limit deflection of the outboard flap relative to the inboard flap during movement of the inboard flap in the chordwise extension direction and movement of the outboard flap in the chordwise extension direction, to provide relative alignment of the inboard flap and outboard flap.

A system and method are provided that enable joined materials to expand and contract at different rates while maintaining a structurally sound connection. A system for joining structures with differing coefficients of thermal expansion includes: a first structural element of a first material having a first coefficient of thermal expansion (CTE); a plurality of flexures each defining a first portion and a second portion and attached at the first portion to the first structural element; and a second structural element of a second material having a second CTE, where the second structural element is attached to the second portion of each of the plurality of flexures, where in response to relative movement between the first structural element and the second structural element, the plurality of flexures bend to accommodate the relative movement.

A composite structural element comprising a substantially planar main section defining a coordinate system with a first axis extending along a longitudinal axis of the structural element and a second axis extending perpendicular to the longitudinal axis within the planar main section. The structural element contains a basic lay-up of single plies, each comprising a fiber-reinforced composite material with a substantially unidirectional fiber orientation. The lay-up comprises N plies arranged from top to bottom in the following form: [[α, β]M; [γ]K; [β, α]M], wherein α, β and γ represent one ply having an angle enclosed between the first axis and the unidirectional fiber orientation of the one ply, respectively, [x]y means y plies each having angle x; [x, y]z means z pairs of plies, K and M are both positive integers equal to or greater than 1: N=4.Math.M+K.

In one aspect, a heating tool includes a heat source having a discharge outlet; and a manifold including an intake conduit configured to releasably connect to the discharge outlet of the heat source and a chamber coupled to the intake conduit having a ventilation path. The chamber includes a diverging portion configured to provide uniform airflow through the ventilation path to provide heating to a surface. In an embodiment, the chamber has a first portion and a second portion configured for assembly and disassembly. A method of curing an aircraft component is provided.

Aircraft wing assemblies are disclosed herein. An example apparatus disclosed herein includes a trailing edge of a wing of an aircraft. The trailing edge has an elastically deformable skin defining a first surface. The trailing edge has a first end to be fixed to the wing and a second end opposite the first end that is to move relative to the first end. A flap is movably coupled to the second end of the trailing edge. The flap is movable between a stowed position and a deployed position. The trailing edge is to elastically elongate when the flap moves from the stowed position to the deployed position and the trailing edge is to elastically collapse when the flap moves from the deployed position to the stowed position.