发明名称 Composite intersection reinforcement
摘要 An assembly and method for manufacturing a composite reinforcement for unitizing a structure are provided. According to one embodiment, the assembly includes a base 32 having a plurality of pins 34 extending outwardly therefrom to define a structure about which a composite fiber is wound to define a composite reinforcement preform 14. The assembly also includes a plurality of mandrels 36 positioned adjacent to the base 32 and at least a portion of the composite reinforcement preform, and a cap 40 that is positioned over at least a portion of the plurality of mandrels 36. The cap 40 is configured to engage each of the mandrels 36 to support the mandrels 36 and the composite reinforcement preform 14 during a curing process to form the composite reinforcement. The base is motor driven for rotation, whilst a continuous composite fibre is dispensed by a winder (24, figure 2 - not shown). The pins 34 may be arranged to provide a figure 8 configuration to the composite fibre. After removal of cap and mandrels, the reinforcement may be cut to a desired shape (cruciform) and prepared for bonding and assembly with other structural components. Reinforcement 14 is capable of being integrated with various structural components (16) that may be assembled into a unitized structure (18) for forming a grid-stiffened structure (20) (figure 1 - not shown).
申请公布号 GB2440642(A) 申请公布日期 2008.02.06
申请号 GB20070014506 申请日期 2007.07.25
申请人 THE BOEING COMPANY 发明人 DAVID T MISCIAGNA;JESSICA J FUHRER;ROBERT S FUNK;WILLIAM S TOLLOTTA
分类号 B29C69/00;B29C53/56;B29C70/08;B29C70/34;B29D99/00 主分类号 B29C69/00
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