A method includes the step placing composite laminate material onto a three dimensional forming tool with an external surface and at least four junctures associated with the external surface. Each juncture is positioned between two adjacent planar surfaces in which each of the two adjacent surfaces extend in a different plane, the junctures converge and each juncture defines a line of direction. The three dimensional forming tool arranged in a two dimensional pattern, has the lines of direction and the two adjacent planar surfaces positioned on opposing sides of each of the at least four junctures are all positioned in a common plane. The line of direction of each of the at least four junctures in the two dimensional pattern converge to a common point. At least one line of direction is not in alignment beyond the common point with another line of direction. Tool apparatus is also provided.

A device for producing a curved fiber preform from a bi- or multidirectional fiber semi-finished product, in particular for an aircraft or spacecraft fuselage component has first lamellae and second lamellae formed to be couplable to one another criss-cross such that they are positioned on a shared plane and thus form a grid. The lamellae at least in part are formed resiliently bendable about an axis intersecting the shared plane such that a local orientation of the lamellae in the grid changes. An adhesion device or structure is formed for temporarily adhering the fiber semi-finished product and is configured such that the local fiber orientation of the fiber semi-finished product also changes accordingly when the lamellae bend.

A device for producing a curved fiber preform from a bi- or multidirectional fiber semi-finished product, in particular for an aircraft or spacecraft fuselage component has first lamellae and second lamellae formed to be couplable to one another criss-cross such that they are positioned on a shared plane and thus form a grid. The lamellae at least in part are formed resiliently bendable about an axis intersecting the shared plane such that a local orientation of the lamellae in the grid changes. An adhesion device or structure is formed for temporarily adhering the fiber semi-finished product and is configured such that the local fiber orientation of the fiber semi-finished product also changes accordingly when the lamellae bend.

The invention relates to a method for producing a folding core (50, 190, 300, 360, 370, 380) for a lightweight structure, wherein in a first method step bending lines (70, 170, 180) are applied onto a deformable flat semi-finished product (40).

The invention is directed to a balanced process for extrusion of a plastic corrugated sheet or blanks, and subsequent converting of the blanks into plastic boxes. The process includes conveying the blanks to a plurality of forming stations for incrementally forming features on the blank needed for forming a box. The present process is performed at a slower speed than typical paper corrugated forming.

The present disclosure provides method, computing device readable medium, and devices for dental appliances formed with folded material components. An example of a method of forming a dental appliance, includes forming a shell having a number of tooth apertures configured to receive and reposition a number of teeth of a patient along one jaw of a patient, the shell having a number of specialized components and wherein the number of specialized components are formed from folding multiple sections of the first sheet of material over each other.

The present disclosure provides method, computing device readable medium, and devices for dental appliances formed with folded material components. An example of a method of forming a dental appliance, includes forming a shell having a number of tooth apertures configured to receive and reposition a number of teeth of a patient along one jaw of a patient, the shell having a number of specialized components and wherein the number of specialized components are formed from folding multiple sections of the first sheet of material over each other.

A composite component adapted to be formed into an aerofoil, a method of forming an aerofoil, an aerofoil, an aircraft wing and a forming jig. The method involves forming a flat layup sheet of plies (1) to be folded about a central leading edge region (6) of the layup into an aerofoil shape, applying to the flat layup (1) one or more layups of plies (9, 10) shaped as spars, partially curing the layup (1) with the spars attached, folding the resulting partially cured composite component (30) about the leading edge region (6) in a forming jig (19) so that opposing edges (4, 5) of the sheet meet as a trailing edge (36) of the aerofoil (35), clamping the jig (19) closed and curing the composite component (30) and adhesive in the forming jig (19) to form the finished aerofoil (35).

A foldable system is described. The system includes a panel consisting of at least two layers, a first flexible layer and a second non-flexible layer, the first and the second layer being attached to each other such that they form a whole, the panel including folds, the folds being applied in the second layer such that the panel can be folded into a predetermined shape. In addition, the first flexible layer includes material with a higher melting temperature than the melting temperature of the second layer.

A foldable system is described. The system includes a panel consisting of at least two layers, a first flexible layer and a second non-flexible layer, the first and the second layer being attached to each other such that they form a whole, the panel including folds, the folds being applied in the second layer such that the panel can be folded into a predetermined shape. In addition, the first flexible layer includes material with a higher melting temperature than the melting temperature of the second layer.