Abstract: A defect recognition procedure in prepreg materials (1) draws a first transversal cross line (4b) at the beginning boundary (3b) of a defective area (2) in a prepreg material (1). A second transversal cross line (4e) at the end boundary (3e) of a defective area (2) is drawn as well. The cross lines (4b, 4e) form an angle (?) with respect to the prepreg material (1) motion direction (5). Each transversal cross line (4b, 4e) delimiting the beginning and the end of a defective area (2) has identification codes (Bi, Ei).

Abstract: A prepreg peel ply material (21) to be used for improving the surface roughness of a composite laminate (13) comprising a backing paper (23) and a base fabric (27) impregnated with a thermosetting resin, wherein the adherence between the backing paper (23) and the base fabric (27), measured by a peeling off parameter P is comprised between 2.9-3.5 min/N/cm2 and the adherence between the base fabric (27) and the composite material, measured by said parameter P is comprised between 130-160 min/N/cm2. The invention also refers to a method for determining the adaptability to an ATL machine of a prepreg peel ply material (21) including the obtention of said parameter P and to a method for manufacturing a composite component comprising an step of laying-up a peel ply base fabric (27) with an ATL machine as the last layer of said component and even as the first layer.

Abstract: The invention relates to a process for making swaged lighting holes (1) in planar areas of parts (5) made of preimpregnated composite, by means of which the part (5) is arranged between a female tooling (11) with the final shape of the bottom side of the swaged part and a caul plate (19) with the final shape of the top side of the swaged part, except in an area (3) which must be swaged, pressure P1 is applied on the caul plate (19) in the area of the part (5) that must be maintained substantially planar, and pressure P2 is applied by means of a male tooling (17) on the area (3) of the part (5) which must be swaged at a forward speed allowing the flow of the resin during the slippage of the fibers of the material so that it may deform, adapting to the final shape of the female tooling (11).

Abstract: The invention relates to an integrated multispar torsion box structure of composite material for aircraft, comprising a lower skin (12), an upper skin (11), several spars (9), each of which comprises in turn a chord (13) and a web (14), several stringers (10) in the lower skin (12) and several stringers (10) in the upper skin (11), characterized in that the mentioned integrated torsion box structure is achieved by means of joining unitary U-shaped structural elements (15), unitary U-shaped structural elements (16) with a flap and unitary C-shaped structural elements (17) with a flap. The invention also relates to a method for manufacturing an integrated multispar torsion box structure of composite material for aircraft.

Abstract: The invention relates to a process for making swaged lighting holes (1) in planar areas of parts (5) made of preimpregnated composite, by means of which the part (5) is arranged between a female tooling (11) with the final shape of the bottom side of the swaged part and a caul plate (19) with the final shape of the top side of the swaged part, except in an area (3) which must be swaged, pressure P1 is applied on the caul plate (19) in the area of the part (5) that must be maintained substantially planar, and pressure P2 is applied by means of a male tooling (17) on the area (3) of the part (5) which must be swaged at a forward speed allowing the flow of the resin during the slippage of the fibers of the material so that it may deform, adapting to the final shape of the female tooling (11).

Abstract: The invention relates to an integrated multispar torsion box structure of composite material for aircraft, comprising a lower skin (12), an upper skin (11), several spars (9), each of which comprises in turn a chord (13) and a web (14), several stringers (10) in the lower skin (12) and several stringers (10) in the upper skin (11), characterized in that the mentioned integrated torsion box structure is achieved by means of joining unitary U-shaped structural elements (15), unitary U-shaped structural elements (16) with a flap and unitary C-shaped structural elements (17) with a flap. The invention also relates to a method for manufacturing an integrated multispar torsion box structure of composite material for aircraft.

Abstract: A catalyst system is provided. In one aspect, the catalyst system includes one or more polymerization catalysts and at least one activator. The activator comprises one or more heterocyclic nitrogen-containing ligands coordinated to a Group 13 atom, wherein the activator is a reaction product of one or more alkyl substituted Group 13 atom-containing compounds and one or more heterocyclic nitrogen-containing compounds, the one or more heterocyclic nitrogen-containing ligands represented by: wherein each substituent X2, X3, X4, X5, X6, and X7 is independently selected from the group consisting of hydrogen, chlorine, fluorine, iodine, and bromine. The catalyst system may be supported or non-supported.

Abstract: An aluminum activator and catalyst system for olefin polymerization is provided. In one aspect, the catalyst system comprises a polymerization catalyst and an activator comprising two or more heterocyclic nitrogen-containing ligands coordinated to a Group 13 atom. Preferably, the activator is a reaction product of one or more Group 13 atom-containing compounds and one or more heterocyclic nitrogen-containing compounds.

Abstract: An aluminum activator and catalyst system for olefin polymerization is provided. In one aspect, the catalyst system comprises a polymerization catalyst and an activator comprising two or more heterocyclic nitrogen-containing ligands coordinated to a Group 13 atom. Preferably, the activator is a reaction product of one or more Group 13 atom-containing compounds and one or more heterocyclic nitrogen-containing compounds.

Abstract: A catalyst system is provided. In one aspect, the catalyst system includes one or more polymerization catalysts and at least one activator.