A method for forming a laminate by stacking sheet materials containing reinforcing fibers includes a fixation step wherein a first region of the laminate in the length direction is fixed to a forming mold having a curved part which comprises at least either a convex shape or a concave shape in a predetermined direction; forming steps wherein the laminate is formed along the surface shape of the forming mold by pressing a second region of the laminate in the length direction, the first region of said laminate having been fixed in the fixation step, against the forming mold by means of a forming jig; and an installation step wherein a holding jig, which holds a state where the laminate is pressed against the curved part, is installed onto the curved part, while maintaining the state where the laminate is pressed against the forming mold by means of the forming jig.

A method for forming a laminate by stacking sheet materials containing reinforcing fibers includes a fixation step wherein a first region of the laminate in the length direction is fixed to a forming mold having a curved part which comprises at least either a convex shape or a concave shape in a predetermined direction; forming steps wherein the laminate is formed along the surface shape of the forming mold by pressing a second region of the laminate in the length direction, the first region of said laminate having been fixed in the fixation step, against the forming mold by means of a forming jig; and an installation step wherein a holding jig, which holds a state where the laminate is pressed against the curved part, is installed onto the curved part, while maintaining the state where the laminate is pressed against the forming mold by means of the forming jig.

The invention concerns a method for producing a carbon fibre, that comprises a step of preparing a continuous fibre made of cellulose from cotton fabrics, by extracting, from these fabrics, cotton in the form of short, discontinuous fibres, and implementing a solvent spinning process; this step being followed by a step of carbonising said obtained continuous fibre made from cellulose, in order to form a carbon fibre. This carbon fibre can be used, in particular, for producing articles made from composite material made from carbon fibres and polymer organic resin.

A method of forming parts uses a forming tool having a forming surface, and an ultrasonic transducer array on the forming surface.

A bed board for a diagnostic bed of a medical examination apparatus is formed in a material that includes basalt fibers. The bed board may have a bed board body composed of basalt fibers and a filler in a predetermined ratio, or may be formed by a hollow shell, composed of basalt fibers and a binder in a predetermined ratio, with the hollow shell being filled by a filler material.

A zero-Poisson-ratio honeycomb structure and an interlocking assembly manufacturing method thereof are provided. The honeycomb structure is formed by combining a four-pointed star shaped structure and horizontal and vertical honeycomb wall arrays at star corners. The zero-Poisson-ratio honeycomb structure not only has the zero-Poisson-ratio characteristic, but also can achieve respective design of in-plane and out-of-plane mechanical properties. Meanwhile, due to the existence of the horizontal honeycomb walls and the vertical honeycomb walls, the connection of multiple honeycomb walls at angular points in the honeycomb structure is avoided. Moreover, a novel manufacturing mode is provided for the honeycomb structure in addition to prepare the honeycomb structure by utilizing a 3D printing process. The honeycomb structure can be manufactured by combining an interlocking assembly process with resin matrix composites. The performance of the honeycomb structure is further improved at the material level.

A zero-Poisson-ratio honeycomb structure and an interlocking assembly manufacturing method thereof are provided. The honeycomb structure is formed by combining a four-pointed star shaped structure and horizontal and vertical honeycomb wall arrays at star corners. The zero-Poisson-ratio honeycomb structure not only has the zero-Poisson-ratio characteristic, but also can achieve respective design of in-plane and out-of-plane mechanical properties. Meanwhile, due to the existence of the horizontal honeycomb walls and the vertical honeycomb walls, the connection of multiple honeycomb walls at angular points in the honeycomb structure is avoided. Moreover, a novel manufacturing mode is provided for the honeycomb structure in addition to prepare the honeycomb structure by utilizing a 3D printing process. The honeycomb structure can be manufactured by combining an interlocking assembly process with resin matrix composites. The performance of the honeycomb structure is further improved at the material level.

A system for manufacturing a part includes a mold having a contoured forming surface. The system also includes at least one tension strap, configured to attach to a consolidated laminate sheet, and a heating assembly, positioned relative to the mold and configured to supply heat to the consolidated laminate sheet, when attached to the at least one tension strap, to form a heated consolidated laminate sheet. The system additionally includes a strap retraction mechanism, configured to retract the at least one tension strap, when attached to the consolidated laminate sheet, to force the heated consolidated laminate sheet against the contoured forming surface of the mold. The heating assembly includes a flexible heating element configured to flex to conform to a shape of the heated consolidated laminate sheet as the heated consolidated laminate sheet is forced against the contoured forming surface of the mold.

A system for manufacturing a part includes a mold having a contoured forming surface. The system also includes at least one tension strap, configured to attach to a consolidated laminate sheet, and a heating assembly, positioned relative to the mold and configured to supply heat to the consolidated laminate sheet, when attached to the at least one tension strap, to form a heated consolidated laminate sheet. The system additionally includes a strap retraction mechanism, configured to retract the at least one tension strap, when attached to the consolidated laminate sheet, to force the heated consolidated laminate sheet against the contoured forming surface of the mold. The heating assembly includes a flexible heating element configured to flex to conform to a shape of the heated consolidated laminate sheet as the heated consolidated laminate sheet is forced against the contoured forming surface of the mold.

A plastic composite material panel includes a roof plate portion adhesively bonded to a first bonding portion provided in a vehicle body frame. A roof extension portion extends from an edge of the roof plate portion and is adhesively bonded to a second bonding portion provided in the vehicle body frame.