A method for assembling a box structure includes elementary parts assembled along an understructure of stiffeners and skins. The understructure and skins are made of composite material with a polymer matrix. The method includes sizing the box structure for the loads to which it is subjected and for a glued assembly. A map of the loads on the structure is obtained and a first load limit is defined depending on the probability of the structure being damaged. The understructure and the skins are assembled by gluing them. An additional layer is applied that covers the assembled elementary parts to areas of the assembled box structure where the first load limit is reached.

A method of manufacturing an aerodynamic structure, for example, an aircraft wing tip, is disclosed. The method includes providing an upper cover having a plurality of lugs, providing a lower cover having a plurality of lugs, measuring the distance between a lug on the upper cover and corresponding lug on the lower cover, selecting, from the plurality of different sized links, a link suitably sized to correspond to the measured distance between the lug on the upper cover and corresponding lug on the lower cover, connecting the selected link to the lug on the upper cover and corresponding lug on the lower cover; and repeating those steps such that each lug on the upper cover is joined to a corresponding lug on the lower cover.

Flexural digital materials are discrete parts that can be assembled into a lattice structure to produce an actuatable structure capable of coordinated reversible spatially-distributed deformation. The structure comprises a set of discrete flexural digital material units assembled according to a lattice geometry, with a majority of the discrete units being connected, or adapted to be connected, to at least two other units according to the geometry. In response to certain types of loading of the structure, a coordinated reversible spatially-distributed deformation of at least part of the structure occurs. The deformation of the structure is due to the shape or material composition of the discrete units, the configuration of connections between the units, and/or the configuration of the lattice geometry. Exemplary types of such actuatable structures include airplane wing sections and robotic leg structures. An automated process may be employed for constructing an actuatable structure from flexural digital materials.

A structure comprising a space frame including a plurality of strut sections which cross at one or more locations within the space frame to define a node at each respective crossing location, wherein the strut sections are laminates comprising a plurality of ply layers, and wherein the ply layers of the crossing strut sections are interleaved at the node(s). Also a method of forming the structure. Also An aerofoil structure, comprising a space frame defining a cage adapted to receive upper and lower covers so as to form upper and lower aerodynamic surfaces of the aerofoil, and at least one spar extending generally spanwise across the structure, wherein the spar includes a spar web and upper and lower spar caps, and wherein the spar web is disposed on one of an interior or exterior side of the cage, and the spar caps are attached to the other of the interior or exterior side of the cage.

A structure comprising a space frame including a plurality of strut sections which cross at one or more locations within the space frame to define a node at each respective crossing location, wherein the strut sections are laminates comprising a plurality of ply layers, and wherein the ply layers of the crossing strut sections are interleaved at the node(s). Also a method of forming the structure. Also An aerofoil structure, comprising a space frame defining a cage adapted to receive upper and lower covers so as to form upper and lower aerodynamic surfaces of the aerofoil, and at least one spar extending generally spanwise across the structure, wherein the spar includes a spar web and upper and lower spar caps, and wherein the spar web is disposed on one of an interior or exterior side of the cage, and the spar caps are attached to the other of the interior or exterior side of the cage.

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. Fabric-coupling members connect wing fabric to the wing-rib assemblies. 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. The method comprises the steps of providing a cable connected assembly and a cable release mechanism coupled to the body of an aircraft; and providing a fabric covering the wings of the aircraft.

Systems, devices, and methods including a wing panel; a spar disposed in the wing panel, where the spar comprises: an upper cap; a lower cap; a honeycomb core connected between at least a portion of the upper cap and the lower cap; an inner face sheet; and an outer face sheet, where at least a portion of the honeycomb core is disposed between the inner face sheet and the outer face sheet.

Systems, devices, and methods including a wing panel; a spar disposed in the wing panel, where the spar comprises: an upper cap; a lower cap; a honeycomb core connected between at least a portion of the upper cap and the lower cap; an inner face sheet; and an outer face sheet, where at least a portion of the honeycomb core is disposed between the inner face sheet and the outer face sheet.

A leading-edge arrangement for a flow body has a curved skin panel having outer and inner sides, and a three-dimensional reinforcing lattice. The curvature of the outer side of the lattice corresponds to the curvature of the inner side of the skin panel. The outer side of the lattice has attachment points connected to the inner side of the skin panel. The lattice is constructed as a three-dimensional framework having a interconnected framework members that form at least one layer of interconnected three-dimensional bodies.

A leading-edge arrangement for a flow body has a curved skin panel having outer and inner sides, and a three-dimensional reinforcing lattice. The curvature of the outer side of the lattice corresponds to the curvature of the inner side of the skin panel. The outer side of the lattice has attachment points connected to the inner side of the skin panel. The lattice is constructed as a three-dimensional framework having a interconnected framework members that form at least one layer of interconnected three-dimensional bodies.