Patent ID: 8262969
Filing Date: 2012-09-11
Classification: B29C,B29L

Abstract:
1. A method of forming a composite aircraft part, the method comprising: placing composite material onto a surface of a tooling, wherein at least a portion of the surface of the tooling is contoured, forming a channel; placing a solid, monolithic bladder onto the composite material relative the channel, wherein the size and shape of the channel corresponds to the size and shape of the bladder and the composite material between the channel and the bladder; choosing a size and elastomer material properties of the bladder, prior to placing the bladder onto the composite material, using finite element analysis (FEA), such that the bladder expands to exert a desired pressure against at least a portion of the composite material during curing; placing additional composite material over the bladder; vacuum-sealing the composite material and the bladder with the tooling; and curing the vacuum-sealed composite material and bladder, thereby forming the part.