Abstract: A molding device includes: a lower mold that supports a workpiece containing a thermoplastic resin and that is heated to a first predetermined temperature; an upper mold that is opposed to the lower mold, that presses the workpiece, and that is heated to a second predetermined temperature; a transferer that moves the lower mold and the upper mold relative to each other in a transfer direction of the workpiece; and control circuitry. The lower mold includes temperature-controlled regions adjacent to one another in the transfer direction, the temperature-controlled regions including a first lower mold temperature-controlled region and a second lower mold temperature-controlled region having a temperature lower than a temperature of the first lower mold temperature-controlled region. The control circuitry changes proportions of the first and second lower mold temperature-controlled regions in the lower mold as a function of a relative position between the upper and lower molds.

Abstract: A first laminated body is worked to form a second laminated body, the first laminated body being formed by laminating prepregs including reinforcing fibers and resin, the second laminated body including a flat portion and a wavy portion, the flat portion being located at at least one of side edge portions of the second laminated body, the wavy portion being located at a portion adjacent to the side edge portion and extending along a longitudinal direction. An intermediate product is formed from the second laminated body by a forming die such that the flat portion becomes a bent portion that is an inside portion whose circumferential length is shorter in a curved portion, and the wavy portion becomes a bent portion that is an outside portion whose circumferential length is longer in the curved portion.

Abstract: 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.

Abstract: A first laminated body is worked to form a second laminated body, the first laminated body being formed by laminating prepregs including reinforcing fibers and resin, the second laminated body including a flat portion and a wavy portion, the flat portion being located at at least one of side edge portions of the second laminated body, the wavy portion being located at a portion adjacent to the side edge portion and extending along a longitudinal direction. An intermediate product is formed from the second laminated body by a forming die such that the flat portion becomes a bent portion that is an inside portion whose circumferential length is shorter in a curved portion, and the wavy portion becomes a bent portion that is an outside portion whose circumferential length is longer in the curved portion.

Abstract: A composite-material aircraft structure includes: a laminated structure formed by laminating composite-material layers; and a curved structure having a circumferential length difference in a longitudinal direction. The laminated structure is maintained in the entire part including the curved structure. In each of the composite-material layers, the reinforced fiber is constituted by a single continuous fiber not including a joint portion and includes a partial slit portion and a notch portion that is the slit portion in an open state.

Abstract: 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.