A film tube installed and sealed in a hollow composite part acts as an internal vacuum bag that eliminates the need for an internal mandrel to react compaction forces applied by autoclave pressure during curing of the part.

A composite structure (1) for an aircraft, having at least one insert (2) for receiving attachment devices, each insert (2) includes a core (3) having a major dimension and containing at least one through-hole (4), and a composite strip arrangement formed by a first section (5) surrounding the core (3) and attached to said core (3) by an adhesive polymeric layer, and a second section (6) including at least one free end (6a). The first (5) and the second portion (6) of the composite strip arrangement are disposed over a first surface (1a) of the composite structure (1), such that the major dimension of the core (3) is positioned transversal to said first surface (1 a). The at least one insert (2) is co-cured with the composite structure (1).

A method for joining a first component and a second component. The method includes forming a first bond between the first component and the second component by providing a plurality of projections on the first component and embedding the plurality of projections in the second component; creating a fastener hole which passes through the first component and the second component and which encompasses at least one of the projections; and forming a second bond between the first component and the second component by installing a fastener in the fastener hole.

A composite member comprises first and second elongate composite elements. Each has a wedge shaped end with a complimentary tapered end surface. At least one of the components is formed of a stack of fiber layers impregnated in resin, with the tapered end surface being formed by each fiber layer extending longitudinally progressively further than the adjacent layer towards the thin end of the wedge at which the fiber layers have the greatest longitudinal extent. The components are joined at their tapered ends by an adhesive, and the properties of the cured composite material of the at least one component and/or the properties of the adhesive are different in the vicinity of the thin end of the wedge as compared to the rest of the tapered surface in order to reduce the stress concentrations in this region.

An image displaying device includes a background layer and a display layer. The display layer includes an inner surface and an outer surface. The inner surface is substantially smooth, and the outer surface includes a plurality of raised areas and recessed areas. The display layer has a first zone with a first thickness measured between the inner surface and a raised area and a second zone with a second thickness measured between the inner surface and a recessed area. The display layer also includes a coloring agent having a higher concentration in the first zone as compared to the second zone. The display layer has increased light transmissivity through the recessed areas and decreased light transmissivity through the raised areas such that a contrast of light transmissivity between the raised and recessed areas generates an image.

Composite laminate structures are produced using partially cured parts. Partial curing of the parts is achieved by applying a catalyst to regions of the parts that are to be fully cured. These regions cure at a lower-than-normal temperature while remaining regions of the part remain uncured, allowing them to be co-bonded or co-cured to other structures.

A method for preparing a pre-bond surface of a composite structure includes the steps of: (1) separating a peel ply, co-cured with a composite substrate, from the composite substrate; and (2) transferring an identifiable marking agent from the peel ply to the composite substrate upon separation of the peel ply from the composite substrate. Residue of the peel ply, transferred from the peel ply to the composite substrate upon separation of the peel ply from the composite substrate, is layered on the identifiable marking agent.

Aspects of the present invention relate to systems and methods for customizing microwave energy distribution within a chamber to accommodate various load characteristics. Aspects of the present invention customized configurations of ports, deflectors, waveguides, conducting rods, and slots to shape and distribute energy.

Disclosed are thermoset/thermoplastic composites that include a thermoset component directly or indirectly bonded to a thermoplastic component via a crosslinked binding layer between the two. The crosslinked binding layer is bonded to the thermoplastic component via epoxy linkages and is either directly or indirectly bonded to the thermoset component via epoxy linkages. The composite can be a laminate and can provide a route for addition of a thermoplastic implant to a thermoset structure.

The invention relates to a component (1) having a fastening region (2) for a threaded connection, wherein the component has a surface (3) having fiber material (5) embedded and integrated into a matrix (4) in at least one layer, wherein the fiber material has a fiber course substantially parallel to the surface, wherein the surface has a fastening opening (6) having a center axis (7) arranged at an angle to the surface and wherein the fastening opening is provided for an internal thread (8). In the region of the fastening opening, the fiber material lying parallel to the surface is deflected, starting from the surface, in such a way that the fiber course of the fiber material after the deflection is at an angle to the surface that approaches the direction of the center axis. Furthermore, a tube (9) is formed by means of the deflected fiber material. The invention further relates to a molded part and to a fastening part for such components.