A polar plate is fabricated. The polar plate is flexible and made of a plastic graphite composite. No matter a supporting member is used for calendering or not, a thin polar plate with controllable thickness is fabricated. The polar plate is excellent in blocking the through-transmission of vanadium ions and the limit of blending ratio of conductive carbon is broken through. The longitudinal through-transmission volume resistivity (proportional resistance to thickness) is greatly improved by adjusting the blending ratio of conductive carbon for meeting the demand of conductivity. In the mean time, the present invention strengthens the rigidity required for the thin polar plate while providing large-area polar plate fabrication for industrial use and convenience and provides a cooling and pressing method for patterning a composite polar plate. An integrated mold is thus obtained to replace the conventional polar plate which needs to be processed and prepared with runner.

A three-dimensional object comprises stacked substrate layers infiltrated by a hardened material comprising engineered powder that is transformed into a substance that flows and subsequently hardens into the hardened material in a spatial pattern that infiltrates positive regions, and does not infiltrate negative regions, in the substrate layers. The powder may be emulsion aggregation powder, chemically-produced toner powder, or a combination. It may be a thermoplastic or thermosettable polymer and may include nylon, elastomers, polyolefins, polyethylene, polyether ether ketone, polyimide, polyetherimide, polyphenylene sulfide, polystyrene, polypropylene, polymethyl methacrylate, and polyaryletherketone, or a combination. The powder particles may have a pre-specified controlled shape and/or a non-homogenous composition. Surface treatments and/or additives may be used to control powder flow and charge distribution. Each substrate layer may be a sheet-like structure comprising fibers held together by binder. The binder may include sodium silicate.

A molding method is provided for manufacturing a composite material having a base layer formed of at least one first prepreg sheet and a second prepreg sheet stacked on at least a portion of the first prepreg sheet. The first prepreg sheet and the second prepreg sheet are stacked, and then heated and cured. The second prepreg sheet constitutes a front surface layer that is integrally formed on the surface of the base layer. Here, the amount of second resin in the second prepreg sheet is larger than the amount of first resin in the first prepreg sheet on a per unit volume basis in an interface between the first prepreg sheet and the second prepreg sheet when the second prepreg sheet is stacked on the first prepreg sheet.

An injection molding system includes a first unit that has a first injection molding machine configured to inject a first molding material into a first cavity partitioned by a first fixed mold and a movable mold, a second unit that includes a second injection molding machine configured to inject a second molding material into a second cavity partitioned by a second fixed mold and the movable mold, and a movement mechanism configured to, after the first molding material is injected into the first cavity, move the movable mold filled with the first molding material from the first injection molding machine to the second injection molding machine.

An aircraft structure (such as a T-shaped structure, a convex structure, a curved structure, or the like) includes: a laminated structure including composite-material layers that are laminated; and wherein the composite material aircraft structure is a three-dimensional structure that includes at least one of a standing structure, a convex structure, or a curved structure. The composite-material layers include at least a composite-material layer in which a reinforced fiber is a single continuous fiber, wherein the single continuous fiber includes a partial slit region. When a thickness of a flat-plate formed body including a same laminated structure as the aircraft structure but not including the three-dimensional structure, is defined as a reference thickness, the aircraft structure includes a thin plate region which has a thickness that is smaller than the reference thickness while maintaining the laminated structure.

A process for preparing a composite part, the process comprising: recovering unsaturated resin prepreg scrap; combining the recovered unsaturated resin prepreg scrap with a second resinous thermosetting component; and co-molding the prepreg scrap and resinous thermosetting component together under a pressure of 25 to 4000 psi and at a temperature of 100-400 F.

A secondary battery configured to have a structure in which an electrode assembly is received in a battery case together with an electrolytic material, wherein the battery case is provided therein with a space for receiving the electrode assembly and wherein the battery case is made of a thermoplastic resin, which can be injection-molded. An injection mold may be formed such that the size of the mold corresponds to the thickness of the electrode, thereby solving a problem in which the formability of a conventional laminate sheet including a metal layer is low. In addition, a process of forming the laminate sheet and a process of sealing the battery case using a pressing member, which are essentially required in order to use the laminate sheet, may be omitted, whereby a manufacturing process is simplified and thus productivity is improved.

An impregnated fibrous material including at least one fibrous material of continuous fibers and: at least one non-reactive thermoplastic polymer matrix, or at least one reactive thermoplastic prepolymer, which is a precursor of the non-reactive thermoplastic polymer, optionally mixed with a chain extender, wherein the at least one non-reactive thermoplastic polymer or the reactive prepolymer is an amorphous polymer or prepolymer having a glass transition temperature such that Tg80 C., or is a semi-crystalline polymer or prepolymer having a melting temperature Tf150 C., the fiber content in the pre-impregnated fibrous material being between 45 and 65 volume %, and the average thickness of the impregnated fibrous material being less than or equal to 100 m, independently of the number of fibers present in the fibrous material before impregnation.

A three-dimensional (3D) object production process comprising providing a thermoset printing apparatus comprising a mixing chamber to receive and mix at least a first reactive component and a second reactive component to provide a thermosetting material, an extrusion nozzle to deliver the thermosetting material to form a 3D object, at least one actuator coupled to the extrusion nozzle to move the extrusion nozzle when delivering the thermosetting material to form the 3D object, and a controller comprising one or more processors and coupled to the extruded thermoset printing apparatus, and depositing the thermosetting material to form the 3D object, wherein the depositing comprises depositing a first layer of thermosetting material and depositing an at least second layer of thermosetting material, wherein the beads of thermosetting material in the at least second layer are offset from the beads of thermosetting material in the first layer.

A process for producing a molded part from a highly filled thermosetting starting material including: introducing the starting material into a prepressing tool; producing a preform from the starting material, the starting material being brought to a prepressing temperature by the prepressing tool and being compressed with a prepressing force to form the preform; removing the preform from the prepressing tool and introducing the preform into a finish pressing tool; and producing a finished part from the preform, the preform being brought to a finish pressing temperature by the finish pressing tool and being compressed with a finish pressing force to form the finished part. Here, the prepressing temperature is lower than the finish pressing temperature and the finish pressing temperature is at least as high as an onset temperature of a curing reaction of the starting material.