Abstract: A novel method and apparatus are provided for consolidating and perforating multilayer laminates by a combination of vibratory motion and impacting pressure applied by a special compacting tool preparatory to final cure.

Abstract: A one-piece composite material torque box for the thrust reverser assembly of a jet engine. The torque box is made up of three composite material subassemblies, a generally planar flange subassembly, a tubular torque tube subassembly, and a cap subassembly. The flange subassembly is configured to transmit tension loads from the cascades of the reverser assembly to the V-blade ring which engages the engine, and the fibers in the composite material are aligned with these load paths. The torque tube subassembly is mounted to the flange subassembly, and is configured to transmit torsion loads from the actuators of the reverser assembly to the upper and lower latch members of the engine assembly; the fibers of the composite material therein are aligned at 45.degree. angles to the tube axis, so as to be in alignment with paths of the tension/compression components of the torsion loads.

Abstract: A fire wall constructed of a composite materials (10) includes a fire-protecting layer of intumescent material (16) integrated into the structure thereof. A plurality of layers of composite material (18) are laminated together to form the fire wall. An outer layer (14) is a shielding material such as fiber glass. Another layer (16) is an intumescent material in juxtapositional relationship between the outer shielding layer (14) and the composite layers (18). The shielding layer (14) and the intumescent layer (16) are co-cured with the composite layers (18) to make a fire wall having integrated fire-protection that is immediately usable without need of additional thermal protection materials.