Abstract: A manufacturing method of composite articles is provided by which it is possible to constantly mold thick composite articles as primary structure component parts for aircraft, such as rotor hubs of helicopters, which are highly accurate in dimensions and have a favorable internal quality with no internal defects such as molding cracks, voids and so forth. Therefore, this manufacturing method of composite articles includes the steps of laying up resin-impregnated reinforcing fiber materials in a molding cavity within a molding jig of a matched die type, evacuating the interior of the molding jig so that the resin-impregnated reinforcing fiber materials are under reduced pressure and thereafter closing and heating the dies of the molding cavity, causing the resin to overflow from the laid up materials into a trap located remote from the molding cavity, and molding the laid up materials inside of the molding jig.

Abstract: The apparatus includes a pair of molds each having a peripheral flange provided with a mating surface. The molds are clamped by a suitable number of clamp assemblies for clamping the flanges of the molds so that the molds are secured together with the mating surfaces in contact with each other. The clamp assembly includes a pair of clamp members for engagement with the flanges of the molds, a shaft passing through the clamp members, a first stop member provided on the shaft for engagement with one of the clamp members, a spacer provided on the shaft for axial slidable movement and adapted for engagement with the other of the clamp members, a second stop member provided on the shaft for engagement with the spacer at an end opposite to the other of the clamp members.

Abstract: An apparatus for molding and curing a resin matrix composite material under pressure and heat by a use of a bag provided in an autoclave for covering the material and applying the pressure to the material.