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.

A method of forming a composite member, includes: applying pressure and heat with a compaction tool to a portion of an uncured composite member to decrease a thickness of the portion, the heat applied with the compaction tool being at a temperature less than a curing temperature of the uncured composite member; and curing the uncured composite member after applying pressure and heat.

A shear tie connector system for securing a frame component to a composite fuselage skin, which includes a shear tie connector and a fuselage mandrel, which defines a slot within which the shear tie connector is positioned.

A method of forming a reinforced panel may include engaging a reinforcement component having a faying surface with a first portion of a heated press, engaging an uncured panel component with an opposing second portion of the press, the panel component having a faying surface complementarily-configured with respect to the faying surface of the reinforcement component, treating the faying surface of the reinforcement component such that the faying surface is active for co-bonding with respect to the panel component, actuating the press to direct the first and second portions of the press toward each other, such that the faying surfaces are complementarily engaged under pressure; and heating the first and second portions of the press to a curing temperature associated with the panel component to substantially simultaneously co-bond the faying surfaces of the reinforcement component and the panel component together, cure the panel component, and form the reinforced panel.

A device (10) comprising a carrier material (14) and a matrix material (12) deposited onto the carrier material in a pattern that leaves a predetermined amount of space (18) between each deposition of matrix material.

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.

A method for plasma treating a surface of a first substrate is disclosed. The method may comprise generating a plasma flume using a plasma treatment device having a nozzle. The plasma flume may emanate through a flume aperture of the nozzle at an emanation angle of about 5 degrees or less. The emanation angle may be defined as an angle between a central axis of the nozzle and a central axis of the flume aperture. The method may further comprise plasma treating the surface of the first substrate with the plasma flume by scanning the plasma flume over the surface of the first substrate. The first substrate may be one of a consolidated thermoplastic material and a cured thermoset material.

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).

An automated fiber-placement method comprises delivering a first quantity of pulsed energy to first portions of at least one fiber-reinforced tape strip, and delivering a second quantity of pulsed energy to second portions of at least the one fiber-reinforced tape strip, alternating with the first portions. Each one of the second portions at least partially overlaps two adjacent ones of the first portions such that overlapping regions of the first portions and the second portions have a higher temperature than non-overlapping regions of the first portions and the second portions. The automated fiber-placement method further comprises laying down at least the one fiber-reinforced tape strip against a substrate along a virtual curvilinear path, such that (i) at least the one fiber-reinforced tape strip is centered on the virtual curvilinear path, and (ii) the overlapping regions are transformed into discrete tape-regions, geometrically different from the overlapping regions.

An automated fiber-placement method comprises delivering a first quantity of pulsed energy to first portions of at least one fiber-reinforced tape strip, and delivering a second quantity of pulsed energy to second portions of at least the one fiber-reinforced tape strip, alternating with the first portions. Each one of the second portions at least partially overlaps two adjacent ones of the first portions such that overlapping regions of the first portions and the second portions have a higher temperature than non-overlapping regions of the first portions and the second portions. The automated fiber-placement method further comprises laying down at least the one fiber-reinforced tape strip against a substrate along a virtual curvilinear path, such that (i) at least the one fiber-reinforced tape strip is centered on the virtual curvilinear path, and (ii) the overlapping regions are transformed into discrete tape-regions, geometrically different from the overlapping regions.