A hybrid preform comprises a bundle of unidirectionally aligned fibers, and at least one partial cut that extends part of the way, but not all of the way, through a transverse cross section of the bundle of fibers at least one location along the length of the bundle.

A semi-finished product for the manufacture of a structural component has a plurality of prepreg tapes, each having unidirectionally arranged reinforcing fibers embedded in a thermoplastic matrix material, and with a plurality of connecting strands containing a thermoplastic material. The prepreg tapes and the connecting strands are either joined to form a textile sheet structure or the prepreg tapes are arranged to form a multiaxial fabric, individual layers of the fabric being joined by the connecting strands. Further, a method for manufacturing a curved structural component from such a semi-finished product is described.

A set of augmented reality (AR) or virtual reality (VR) glasses are disclosed. The glasses comprise a fiber reinforced structure. The fiber reinforced structure includes a continuous fiber component. The fiber reinforced structure also includes a thermoplastic material injection molded over the continuous fiber component, wherein the thermoplastic material surrounds the continuous fiber component. The glasses also comprise electronics that are coupled to the fiber reinforced structure, wherein the electronics are configured to facilitate presentment of imagery onto a lens of the glasses.

A manufacturing method of a halogen-free flame-retardant thermoplastic braided fiber reinforced polymer composite board, comprising steps of: preparing a recycled material containing a halogen-free flame-retardant thermoplastic braided fiber reinforced polymer composite; adding a polymer base material to the recycled material to form a core layer material and extruding the core layer material with a low shear extruder; hot pressing the core layer material by rollers to obtain a recycled fiber core layer; preparing a reinforcement layer containing a fiber material or a fabric with pores; and stacking and hot pressing the recycled fiber core layer and the reinforcement layer.

A conveyor module, small fragments of which are detectable by X-ray and/or magnetic sensors, is formed from a compounded mixture of a polyketone resin, a ferrous metal powder, and, optionally, a barium sulfate powder. The ferrous metal powder is preferably 400 series stainless steel powder, or alternatively, a 300 series stainless steel powder, iron powder, or other iron alloy powder.

A method of manufacturing a fabric structure for use in manufacturing a composite aircraft blade. The method comprises: combining yarns including both reinforcing material filaments and a matrix material with yarns of reinforcing material filaments and/or yarns including at least one filament of matrix material; or by combining yarns of reinforcing material filaments with yarns including at least one filament of matrix material; or by combining yarns each comprising both reinforcing material filaments and matrix material. Combining may comprise weaving, knitting or braiding. The matrix material may be a thermoplastic.

An aircraft structure (such as a T-shaped structure, a convex structure, a curved structure, or the like) includes: a laminated structure including composite-material layers that are laminated; and wherein the composite material aircraft structure is a three-dimensional structure that includes at least one of a standing structure, a convex structure, or a curved structure. The composite-material layers include at least a composite-material layer in which a reinforced fiber is a single continuous fiber, wherein the single continuous fiber includes a partial slit region. When a thickness of a flat-plate formed body including a same laminated structure as the aircraft structure but not including the three-dimensional structure, is defined as a reference thickness, the aircraft structure includes a thin plate region which has a thickness that is smaller than the reference thickness while maintaining the laminated structure.

The disclosure relates to a method for producing a fiber preform, wherein: at least one dry and textile fiber material is provided; the fiber material is assembled into a plurality of individual layers; the plurality of individual layers is provided with a binder; the plurality of individual layers is layered to form a package; and a plurality of interconnected fiber preforms is formed by pressing the package. A separation of the plurality of interconnected fiber preforms and activation of the binder occur in a common process step. The disclosure furthermore relates to a corresponding system.

Methods for microwave melting of fiber mixtures to form composite materials include placing the fiber mixture in a receptacle located in a microwave oven. The methods further include microwave heating the mixture, causing a heat activated compression mechanism to automatically increase compressive force on the mixture, thereby eliminating air and void volumes. The heat activated compression mechanism can include a shape memory alloy wire connecting first and second compression brackets, or one or more ceramic blocks configured to increase in volume and thereby increase compression on the mixture.

Systems for manufacturing a composite structural laminate comprising a conveyor element, a plurality of heating elements, and a plurality of cooling elements. The system may further incorporate a series of cutting elements that distribute constituent laminate elements along the conveyor element. The system provides heating and cooling of the constituent laminate elements which results in improved strength for the resulting laminate.