Composite-material aircraft part and method of manufacturing same

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.

1 . A method of manufacturing a composite-material aircraft structure, the method comprising:
 forming a laminated body by laminating composite-material layers, wherein each composite-material layer includes a reinforced fiber and a resin composition; and   placing the laminated body at a forming die and subjecting the laminated body to heating-pressurizing forming, wherein:   the composite-material layers include a composite-material layer that includes at least a single reinforced fiber and a resin composition, the single reinforced fiber including a slit region, the slit region including partial slits;   the forming die includes a female structure and a male structure fitted to the female structure, and a cavity formed between the male structure and the female structure includes a region where at least one of a standing structure, a convex structure, or a curved structure is formed as a three-dimensional structure; and   the slit region is formed at the composite-material layer such that when the laminated body is placed on the forming die, the slit region is located on at least one of a region corresponding to the three-dimensional structure or a region adjacent to the region corresponding to the three-dimensional structure.   
     
     
         2 . The method according to  claim 1 , wherein when the composite-material layer including the slit region is referred to as a first composite-material layer, the composite-material layers include a second composite-material layer which does not include the slit region and includes the resin composition and the single reinforced fiber. 
     
     
         3 . The method according to  claim 1 , wherein the slit region is formed at part of the composite-material layer or the entire composite-material layer. 
     
     
         4 . The method according to  claim 2 , wherein the slit region is formed at part of the composite-material layer or the entire composite-material layer.