A panel assembly is formed by a plurality of bonds between two sheet materials in a face to face relationship to form a preform. The plurality of bonds define a closed perimeter region between the two sheet materials and an open perimeter region between the two sheet materials. The preform may be formed into a predefined shape. Pressurized fluid is applied through an inlet into the open perimeter region to expand the preform. The pressurized fluid expands the open perimeter region such that the two sheet materials expand in an opposing direction, thereby defining an expanded open perimeter region. The closed perimeter region between the two sheet materials remains vacant of the pressurized fluid such that the closed perimeter region is not expanded. The expanded open perimeter region is filled with a filler material for improving a performance characteristic of the panel assembly, e.g., strength, sound absorption, or stiffness.

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.

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.

A method for forming a metal composite film for battery cells includes at least the following steps: (a) inserting the metal composite film into a forming apparatus having a recess; (b) fixing the metal composite film in place by closing a film holder; (c) preforming the metal composite film within the recess in a first direction; and (d) final forming of the metal composite film within the recess in a second direction.

The present invention discloses a method for manufacturing a thin-walled metal component by three-dimensional (3D) printing and hot gas bulging. The present invention uses 3D printing to obtain a complex thin-walled preform, which reduces a deformation during subsequent hot gas bulging. The present invention avoids local bulging thinning and cracking, undercuts at the parting during die closing, and wrinkles due to the uneven distribution of cross-sectional materials, etc. The present invention obtains a high accuracy in the form and dimension through hot gas bulging. After a desired shape is obtained by hot gas bulging, a die is closed to keep the component under high temperature and high pressure for a period of time, so that a grain and a phase of the material are transformed to form a desired microstructure.

A manufacturing method for a plate comprising channels in which the method includes a step of superposing the two strips, a step of welding the two strips along the weld seams, a step of blocking the zones between the weld seams on one side of the strips, a pressurization step with a compressed fluid, where the zones between the weld seams open out along another side, to expand the strips, and a step of opening the zones blocked during the blocking step. This manufacturing method enables the titanium strips to be welded together and shaped by pressurization.

The present disclosure discloses a device and a method for forming a metal plate by using a high-energy electric pulse to drive an energetic material. The device includes high-energy pulse discharge equipment, an intelligent robot arm control system, a vacuum pumping device, a hydraulic press, a forming die, positive and negative electrodes, an energetic rod, and liquid supply equipment. According to the present disclosure, energy of a metal wire is added to energy of an energetic material after energy release to implement high-rate forming of the plate. A discharge voltage of the high-energy pulse discharge equipment is reduced and a service life thereof is prolonged. The discharge equipment is triggered by the manufactured small-size electric pulse metal wire, thereby reducing a volume and costs of the equipment and miniaturizing the equipment to implement precise operating, forming, and intelligent integration with the robot arm control system.

The present disclosure discloses a device and a method for forming a metal plate by using a high-energy electric pulse to drive an energetic material. The device includes high-energy pulse discharge equipment, an intelligent robot arm control system, a vacuum pumping device, a hydraulic press, a forming die, positive and negative electrodes, an energetic rod, and liquid supply equipment. According to the present disclosure, energy of a metal wire is added to energy of an energetic material after energy release to implement high-rate forming of the plate. A discharge voltage of the high-energy pulse discharge equipment is reduced and a service life thereof is prolonged. The discharge equipment is triggered by the manufactured small-size electric pulse metal wire, thereby reducing a volume and costs of the equipment and miniaturizing the equipment to implement precise operating, forming, and intelligent integration with the robot arm control system.

A method for manufacturing an aircraft leading edge panel, includes a step of overmoulding a coating onto a sheet positioned in a cavity of a mould, which cavity is delimited by a shaping surface which exhibits an optimized surface finish. The coating includes, after the overmoulding step, an exterior face which corresponds to the exterior face of the panel that is to be obtained and which exhibits an optimized surface finish conferred by the shaping surface of the mould. A panel may be obtained using this method and a leading edge includes at least one such panel. Because of the optimized surface finish of the exterior surface thereof, the panel contributes to extending the regions of laminar flow.

A method for manufacturing an aircraft leading edge panel, includes a step of overmoulding a coating onto a sheet positioned in a cavity of a mould, which cavity is delimited by a shaping surface which exhibits an optimized surface finish. The coating includes, after the overmoulding step, an exterior face which corresponds to the exterior face of the panel that is to be obtained and which exhibits an optimized surface finish conferred by the shaping surface of the mould. A panel may be obtained using this method and a leading edge includes at least one such panel. Because of the optimized surface finish of the exterior surface thereof, the panel contributes to extending the regions of laminar flow.