The object of the invention is a multichamber structural element manufacturing method which for forming a multichamber structural element with chamber profiles (1) extending radially from the center defined by the connection of the chamber profiles (1) comprises the following steps: at least three chamber profile preforms (2) are provided, wherein each chamber profile preform (2) comprises two walls (3) made of a sheet of metal material and arranged with respect to each other in substantially parallel planes with a gap retained between them, wherein the edges of the individual walls (3) converge, and wherein a valve element (6) is arranged on at least one wall (3); the unconnected wall (3) edges of each of the chamber profile preforms (2) are sealed with a seal (5) for forming a closed hermetic empty inner space of the chamber profile preform (2); a fluid under pressure is introduced through the valve element (6) into the inner space of the chamber profile preform (2) for forming a deformed chamber profile (1), at least three chamber profile preforms (2) or chamber profiles (1) are connected in the area of the corresponding inner edges of the chamber profile preform (2) or the chamber profile (1), proximal with respect to the connection axis (4), along at least part of the inner edges. The object of the invention is also a multichamber structural element.

A component of a vehicle structure is obtained by a hot forming operation on a hybrid panel having a sheet element of light alloy and a sheet of plastic material. The hybrid panel is hot formed by pressing it against a forming surface of a mould element by a pressurized gas or by a second mould element. Following this operation, the hybrid panel assumes a configuration corresponding to the forming surface, whereas the light alloy sheet element and the plastic material sheet constituting the hybrid panel adhere to each other following softening by heat of the plastic material. Before the hot forming step, a surface of said light alloy sheet element which must contact the plastic material sheet is subjected to a roughening treatment, thereby defining surface asperities between which the plastic material of the plastic material sheet is inserted when it is softened by heat.

A method and a device for manufacturing a part starting from a cushion made of deformable material, in particular for an edge of an element of an aircraft. The device includes a preparation unit to create a cushion with two plates and, between the plates, an internal space with an opening, and a molding unit comprising a mold in which the cushion is positioned, the mold comprising two shells and an imprint corresponding to the shape of the part to be manufactured, the molding unit configured to inject a pressurized fluid into the internal space of the cushion through the opening to deform the cushion such that it matches the imprint and forms the part, the device being capable of manufacturing one-piece parts of various sizes, and in particular parts having complex shapes, in particular non-developable shapes.

A method of manufacturing a hollow aerofoil component 100 for a gas turbine engine 10 comprises joining a first panel 200 to a second panel 300 using bonding, and hot forming the panels into shape. The bonding step and the hot forming step are performed in the same rig, thereby optimizing process time and component quality.

There is proposed a method of forming an inflated aerofoil (1), the method comprising the steps of: forming a layered, planar pre-form (30); providing at least one stress-relieving opening (44, 45, 46, 47) through the pre-form; hot creep forming and inflating the pre-form (30) to form an intermediate aerofoil; and subsequently removing material from the intermediate aerofoil, including at least a region containing the or each stress-relieving opening (44, 45, 46, 47), to form a finished aerofoil.

There is proposed a method of forming an inflated aerofoil (1), the method comprising the steps of: forming a layered, planar pre-form (30); providing at least one stress-relieving opening (44, 45, 46, 47) through the pre-form; hot creep forming and inflating the pre-form (30) to form an intermediate aerofoil; and subsequently removing material from the intermediate aerofoil, including at least a region containing the or each stress-relieving opening (44, 45, 46, 47), to form a finished aerofoil.

The present invention relates to a method for manufacturing a product with a spatially structured surface from a semi-finished product, a semi-finished product required for this purpose and a product produced in this way. The method is characterized in that a patterned target bending location is produced in the semi-finished product, and in that the semi-finished product is then subjected to a pressure over its surface, which is dosed in such a way that the pressure causes a plastic deformation of the semi-finished product along the target bending location, so that a product with a spatially structured surface is produced.

The present invention relates to a method for manufacturing a product with a spatially structured surface from a semi-finished product, a semi-finished product required for this purpose and a product produced in this way. The method is characterized in that a patterned target bending location is produced in the semi-finished product, and in that the semi-finished product is then subjected to a pressure over its surface, which is dosed in such a way that the pressure causes a plastic deformation of the semi-finished product along the target bending location, so that a product with a spatially structured surface is produced.

The invention relates to a manufacturing method for a crash frame of a battery compartment for electric drive vehicles by using metallic sheets which are arranged on top of one another and fixed together and which form in a following step a space by using an inner active media forming process to create walls of a crash frame whereby the space works as a deformation space to protect the battery modules inside the battery compartment against an impact. The invention further relates to the use of the crash frame for a battery compartment.

Examples of forming metal composites are described herein. In an example, a metal sheet is formed into a predetermined shape using superplastic thermal forming technique. Further, a carbon fiber-reinforced polymer sheet is shaped into the predetermined shape by thermal forming. The metal sheet and the carbon fiber-reinforced polymer sheet are coupled by applying an adhesive between the metal sheet and the carbon fiber-reinforced polymer sheet, to form a metal composite.