A prepreg comprising: carbon fibers; and a resin composition containing an epoxy resin having a biphenyl structure, a curing agent, and melamine cyanurate.

A method of making the asphalt shingles includes applying a substrate to a layer of shingle-forming material, the substrate having indicators at predetermined spaced-apart distances, with the indicators being sensed as the shingle-forming layer is moved along a predetermined path, with adhesive zones being applied to the shingle such that the application of the adhesive zones is synchronized in response to sensing the locations of the indicators, and with the shingle-forming layer then being cut into individual shingles.

In order to provide a composite good in formability into a three-dimensional shape and easy to manufacture, in a laminate having a core material layer and a skin material laminated on the core material layer, the core material layer has a plurality of plate-shaped flakes lined up along a surface of the skin material, and adjacent plate-shaped flakes are separated from each other by a gap or by a cut in the core material layer, and cutting directions along a thickness direction, which is determined from cutting marks formed on an outer periphery, are identical to each other among the plurality of the plate-shaped flakes.

The present invention relates to a spar cap for a wind turbine blade comprising a plurality of pre-cured fibre-reinforced elements and a plurality of interlayers. The plurality of pre-cured fibre-reinforced elements include a first pre-cured fibre-reinforced element and a second pre-cured fibre-reinforced element and the plurality of interlayers include a first interlayer comprising a first plurality of fibres embedded in a first cured resin. The first interlayer is being arranged between the first pre-cured fibre-reinforced element and the second pre-cured fibre-reinforced element. The first plurality of fibres have a first elastic modulus, the first cured resin has a second elastic modulus, the first and/or second pre-cured fibre-reinforced elements have a third elastic modulus, and the first interlayer has a fourth elastic modulus. The ratio between the first elastic modulus and the second elastic modulus is between 1:4 and 4:1 and/or the ratio between the third elastic modulus and the fourth elastic modulus is between 1:4 and 4:1.

A method of manufacturing a fan blade for a gas turbine engine. The method includes providing a compression mould having an internal mould surface corresponding to an outer profile of a fan blade, providing opposing first and second laminates to form a shell corresponding to the mould surface, each laminate comprising a lay-up of plies of fibre reinforcement material, applying a core material comprising quasi-isotropic short fibre reinforced resin in the compression mould so that with the compression mould in a moulding configuration the core material is enclosed by the shell, the core material and the shell forming a pre-form for the fan blade, applying pressure to compress the pre-form so that it conforms to the mould surface, and applying heat to cure the pre-form.

The present invention addresses the problem of providing a method for molding, using a honeycomb core, a composite material structure that is high-quality, low cost, and leaves less voids. The present disclosure addresses the problem of providing a method for molding, using a honeycomb core, a composite material structure with which it is possible to reduce dimples in a composite material skin at low cost. According to a method for molding a composite material structure of the present disclosure, an uncured composite material honeycomb sandwich panel in which prepreg is laminated on upper and lower surfaces of a honeycomb core via an adhesive is covered with a vacuum bag and placed in an autoclave. After that, the vacuum bag is evacuated and, while the evacuation is being continued, is heated and pressurized by the autoclave to cure a matrix resin of the prepreg and achieve adhesion to the honeycomb core.

An apparatus for fabricating a composite structure includes a tape placement machine including a delivery head configured to dispose a composite tape and a backing plate coupled to the tape placement machine and selectively located relative to the delivery head to react to a placement force applied by the tape placement machine as the composite tape is being disposed.

Embodiments disclosed herein relate to composite laminate structures including a polymer layer having sp.sup.2 carbon-containing material and improved heat release properties, and methods of making the same.

This specification discloses an article of manufacture. The article of manufacture has at least one structural blank and at least one guide. The structural blank has a plurality of oriented fiber plies in a thermoplastic matrix. The guide has a plurality of random dispersed fibers in a thermoplastic matrix. The guide is affixed to the structural blank by injection molding and over molding the guide onto the structural blank. The article of manufacture can take a number of forms for use in industries such as aircraft, automobiles, motorcycles, bicycles, trains or watercraft.

A low cost and disaster relief housing solution includes the combination of preconstructed in-service or out-of-service shipping containers that are integrated with renewable and sustainable materials to complete the buildout of the shipping containers. The embodiment also includes folding solutions that allows for a superior logistic solution for shipping and site integration.