CPC B64F 5/10 (2017.01) [B29C 70/342 (2013.01); B64C 1/061 (2013.01); B64C 1/064 (2013.01); B29K 2307/04 (2013.01); B29L 2031/3082 (2013.01); B64C 2001/0072 (2013.01)] | 8 Claims |
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;
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 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 is curved in a longitudinal direction and includes a placement surface on which the laminated body is placed,
the heating-pressurizing forming includes:
placing the laminated body on the placement surface; and
stretching the laminated body in an in-plane direction while a part of the laminated body is restricted such that a side edge of the laminated body located at one side of the placement surface is restricted, and the laminated body is extended toward the other side of the placement surface in the in-plane direction,
a plane of the laminated body in which the restriction is performed is orthogonal to the in-plane direction, and
an entire portion of the laminated body is restricted in the plane.
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