Composite intersection reinforcement

Abstract

An assembly and method for manufacturing a composite reinforcement for unitizing a structure are provided. According to one embodiment, the assembly includes a base having a plurality of pins extending outwardly therefrom to define a structure about which a composite fiber is wound to define a composite reinforcement preform. The assembly also includes a plurality of mandrels positioned adjacent to the base and at least a portion of the composite reinforcement preform, and a cap that is positioned over at least a portion of the plurality of mandrels. The cap is configured to engage each of the mandrels to support the mandrels and the composite reinforcement preform during a curing process to form the composite reinforcement.

1 - 18 . (canceled) 
     
     
         19 . A composite reinforcement for unitizing a structure, the composite reinforcement comprising:
 a plurality of legs formed of a continuous composite fiber and having at least one intersection, wherein the legs are comprised of a plurality of unidirectional layers positioned one on top of the other, and wherein at least a portion of at least one leg is configured to be secured to at least one structure.   
     
     
         20 . The composite reinforcement of  claim 19 , wherein the continuous composite fiber comprises a cruciform cross section. 
     
     
         21 . The composite reinforcement of  claim 19 , wherein the continuous composite fiber comprises a pre-impregnated tow material or a dry tow material. 
     
     
         22 - 25 . (canceled) 
     
     
         26 . An aircraft structure comprising:
 at least one structural component; and   at least one composite reinforcement comprising a plurality of legs formed of a continuous composite fiber and having at least one intersection, wherein the legs are comprised of a plurality of unidirectional layers positioned one on top of the other, and wherein at least a portion of at least one leg is secured to the at least one structural component to form a unitized grid-stiffened aircraft structure.   
     
     
         27 . The aircraft according to  claim 26 , wherein the at least one structural component comprises at least one of a stiffener, a frame, and a longeron.