A method and apparatus for constructing a tubular assembly 40 comprising an inner portion (24) and a further portion (23) surrounding the inner portion. The inner portion (24) comprises reinforcement (37) and the further portion (23) being formed from a strip (50) of material comprising two opposed longitudinal marginal side portions (53). The apparatus comprises an assembly station (220) comprising a wall (253). The apparatus comprises means for advancing the inner portion (21) along a first path (231) extending passed the wall (253), and means for advancing the strip (50) along a second path (232) and causing the strip to encircle the wall (253) and thereby wrap about and surround the inner portion (21). The apparatus further comprises means (321) for introducing resinous binder into the reinforcement (37) as the strip (50) is being wrapped about the inner portion (21).

A method of manufacturing a wind turbine blade part, such as a spar cap, by means of resin transfer moulding, preferably vacuum assisted resin transfer moulding, where fibre reinforcement material is impregnated with liquid resin in a mould cavity, wherein the mould cavity includes a rigid mould part having a mould surface defining a surface of the wind turbine blade part is described. The method includes the steps of: a) stacking a plurality of fibre reinforcement layers on the rigid mould part forming a fibre reinforcement stack, b) providing at least one flow-enhancing mat in the fibre reinforcement stack, c) sealing a second mould part, against the rigid mould part to form the mould cavity, d) optionally evacuating the mould cavity, e) supplying a resin to the mould cavity, and f) curing or hardening the resin in order to form the wind turbine blade part.

A method for manufacturing a deflection member is disclosed. The method may include the step of incorporating a monomer, a photoinitiator system, a photoinhibitor, and/or a reinforcing member. A further step includes blending the monomer, photoinitiator, and/or photoinhibitor to form a blended photopolymer resin. Further steps may be exposing the photopolymer resin to radiation form a first radiation source and/or a second radiation source.

A cosmetically altered fiberglass piece having an outer layer of curable gel-coat, an intermediate layer of textile fabric having a graphical element depicted thereon, and an inner layer of composite. A resin or epoxy is used to bond the layers to form the cosmetically altered fiberglass piece. Introduction of resin or epoxy is performed through one of a manual application, a vacuum infusion, or light RTM.

A gasket is disclosed for use as an environmental seal between a first aircraft part having planer surface and a second aircraft part having a planer surface, the two planer parts spread apart and engaged with fasteners. The gasket, in some embodiments, is compressible between the planer surfaces. The gasket, in some embodiments, comprises a first tabular portion having tabular portion properties and having a first tabular thickness and a length and a width, the length and width much greater than the first tabular thickness; and a second tabular portion having tabular portion properties having a second tabular thickness, a length and width, the length and width much greater than the second tabular thickness; and a tabular skeleton. The first and second tabular portions and the skeleton are positioned parallel to one another. The skeleton is at least partly contacting one of the tabular portions. The first tabular portion and the second tabular portion differ in at least one tabular portion property.

Embodiments are directed to systems and methods for creating a tubular composite structure. In one embodiment, a device comprises multiple layers of cured composite fabric bonded together to form a tubular composite structure, wherein alternating groups of the multiple layers comprise on-axis fabric and off-axis fabric. The tubular composite structure may form a spar for an aerodynamic component. The composite fabric may comprise one or more of carbon, fiberglass, or other composite materials, or a combination of materials. One or more stacks of the fabric wrap completely around the tubular composite structure, and other stacks of fabric may not wrap completely around the tubular composite structure.

A controlled shear vacuum forming method that includes forming a three-dimensional (3D) structure from a preform material on a molding tool using restraints during vacuuming to prevent wrinkling. The restraints are withdrawn during vacuuming to allowing the preform material to come into contact with the sidewalls of the molding tool in a gradual manner. Such forming method is particularly suitable for forming wing spars with bent sections and/or curved contours.

A desired shape can be easily realized, and a decrease in strength can be inhibited. A method for producing a composite material includes: an insertion step of inserting an inner member in which a second reinforcing fiber is impregnated with a resin into a space of an outer member that is formed of a woven first reinforcing fiber extending in an undulating manner, the outer member including an opening that is provided at at least one end portion and the space that communicates with the opening; and a composite material forming step of forming a composite material in which the outer member and the inner member are joined to each other by curing the resin of the inner member to join the outer member and the inner member to each other.

A fiber-reinforced plastic substrate is described in which a plurality of resins having different properties are firmly compounded and that includes components [A], [B], and [C]: [A] reinforcing fibers; [B] thermoplastic resin (b); and [C] thermoplastic resin (c),
wherein the component [A] is arranged in one direction, in the fiber-reinforced plastic substrate, a resin area including the component [B] and a resin area including the component [C] are present, the resin area including the component [B] is present on a surface of one side of the fiber-reinforced plastic substrate, and a distance Ra.sub.(bc) between Hansen solubility parameters of the component [B] and the component [C] satisfies formula (1):

Ra.sub.(bc)={4(δDB−δDC).sup.2+(δPB−δPC).sup.2+(δHB−δHC).sup.2}.sup.1/2≥8

wherein Ra.sub.(bc), δDB, δDC, δPB, δPC, δHB and δHC are as defined.

A composite includes a heavy Leno weave fabric, a first resin coating, and a second resin coating. The heavy Leno weave fabric has a first side and a second side. The fabric is characterized by yarns having a denier number of at least about 1,300 in both warp and weft directions. The fabric defines a pore structure. The first resin coating is on the first side of the heavy Leno weave fabric. The second resin coating is on the second side of the heavy Leno weave fabric. The first and second resin coatings are bound to each other through the fabric via the pore structure.