| 摘要 |
A mandrel assembly for use in manufacturing composite parts, comprising: a mandrel 105 extending along a mandrel axis and including a mandrel end; an end cap core 104 operatively coupled to and covering the mandrel end 114, the end cap core extending beyond the mandrel end along the mandrel axis; and a non-permeable film 101 encasing the mandrel and the end cap core thereby to substantially seal the mandrel and the end cap core. The end cap may be substantially sealed using a bonding agent 112 or end cap sheath 110. The end cap core may have a passageway 106 fluidly connecting the mandrel with a vacuum source. The end cap core may further include one or more trim-guide attachment points (302, fig 3) such that a trim guide tool may be attached to the end cap core to aid in accurate trimming of the mandrel assembly along a net-dimension trim line 103. The mandrel assembly with preform 102, may be placed in a part tool (512, fig 5) such that it will accurately form a hat stringer and inner mould line of a composite part (509, fig 5) upon resin infusion and cure of the composite part. Embodiments of the disclosure may be used in the context of an aircraft manufacturing and service method (fig 8). The disclosed method and apparatus may be employed to fabricate composite parts such as fuselage sections. |
