| 摘要 |
PROBLEM TO BE SOLVED: To provide a method for manufacturing a stringer (1) for an aircraft skin panel. SOLUTION: This method comprises a process for preparing a bundle (32) of sheet metal band plates (3) bent to have a prescribed cross-sectional shape and alternately arranged with at least one fiber layer (4) impregnated with resin, and a process (70) for applying heat and pressure to the bundle (32) for curing the resin to fix the shape. Thus, a composite laminated stringer is obtained. In order to manufacture the fuselage panel of the composite laminated material provided with the composite laminated stringer, the resin contained in the stringer is cured concurrently with resin existing between metal layers of laminates suitable for forming an outer skin. COPYRIGHT: (C)2004,JPO |
