The method for forming from a round shaped cylinder to a square shaped cylinder or flat sheet which can be inserted in a square or rectangular shape metal pipe includes initiating turning of a heated mandrel, extruding heated polymer, wrapping while compressing a first layer of heated polymer or mesh, disposing a mesh or polymer layer over the cylinder encapsulating the cylinder on the turning mandrel while simultaneously laying a second layer of heated polymer over the turning mandrel and compressing the layer of heated polymer into the mesh layer and the mesh layer into the first layer of heated polymer simultaneously, and repeating the layering of the heated polymer and mesh layer until a desired wall thickness is reached.

Apparatus and systems provide for the construction of wing sections having a plurality of wing spars abutted against each other to form a contiguous multi-box wing spar layup. An aircraft wing includes a plurality of wing spars configured to be attached to an aircraft fuselage, an upper wing surface, and a lower wing surface. The plurality of wing spars are in a multi-box wing spar layup. The plurality of wing spars, the upper wing surface, and the lower wing surface are composite layers having continuous fibers.

A hockey stick apparatus may include a molded blade structure coupled to the proximal end of a hollow shaft structure. The molded blade structure can include: a top edge spaced apart from a bottom edge by a blade height, a heel spaced apart from a toe by a blade length, a front face spaced apart from a back face, and an optional slot defining an aperture extending through front face and the back face. A stiffness of the blade may vary along the blade height by changing the shape of the blade and changing a quadratic momentum of the cross-section along the blade height.

A semifinished product for making a composite fiber molded part is made by first spinning from a row of orifices of a spinning nozzle low-melting fibers of a thermoplastic. These low-melting fibers are then combined into a laminated semifinished product with high-melting reinforcement fibers of the same thermoplastic but having a melting temperature higher than the melting temperature of the low-melting fibers.

A curable resin composition containing: (a) at least one resin; and (b) curative selected from the group consisting of (i) a mixture of at least one low temperature curative and at least one high temperature curative or (ii) a curative that has a low temperature curative part and a high temperature curative part wherein the amount of the low temperature curative is sufficient to cause enough resin-curative addition reaction to effect B-staging in the full resin-curative formulation, the amount of the high temperature curative is sufficient to cause the resin to cure catalytically but insufficient to cause resin-curative addition reaction in the final cure, and the ratio of the resin (a) to the curative (b) is greater than or equal to about 5. The present composition may be used to make prepregs for automotive or aerospace application.

A method of manufacturing a gas tank comprises: a step (a) of preparing a liner having a hollow cylindrical shape; a step (b) of forming a first layer by winding a first fiber bundle impregnated with resin around the liner; a step (c) of forming a second layer by winding a second fiber bundle impregnated with resin around the liner with the wound first fiber bundle in such a manner that portions of the second fiber bundle overlap each other in a direction parallel to a center axis of the liner; a step (d) of causing a section where the portions of the second fiber bundle overlap each other to get into the first layer; and a step (e) of curing the resin.

A system for constructing a composite structure includes a braiding machine, a winding tool and a forming machine. The composite structure is constructed of a wound tubular braiding. The wound tubular braiding is constructed of a biaxial or triaxial tubular braid of unidirectional tape.

A system for constructing a composite structure includes a braiding machine, a winding tool and a forming machine. The composite structure is constructed of a wound tubular braiding. The wound tubular braiding is constructed of a biaxial or triaxial tubular braid of unidirectional tape.

A system for constructing a composite structure includes a braiding machine, a winding tool and a forming machine. The composite structure is constructed of a wound tubular braiding. The wound tubular braiding is constructed of a biaxial or triaxial tubular braid of unidirectional tape.

A composite airfoil is disclosed. In various embodiments, a composite airfoil as disclosed herein includes an outer skin comprising one or more layers of carbon fiber composite material, the outer skin defining an aerodynamic surface having a leading edge; and a reinforcement material comprising a roll of fiberglass reinforced fabric positioned behind the outer skin along at least a portion of the leading edge.