A multilayer radar-absorbing laminate includes three juxtaposed blocks. A first electrically conductive block is arranged toward the inside of the aircraft in use. A second electromagnetic intermediate absorber block has a layer of electrically non-conductive fiber sheets is permeated by graphene-based nanoplatelets to achieve a periodic and electromagnetically subresonant layer, the conductive layers containing graphene nanoplatelets alternating with non-conductive layers. A third block of electrically non-conductive material is arranged towards the outside and forms part of the outer surface of the aircraft. The second block is produced by depositing on the fiber sheets a suspension of graphene nanoplatelets in a polymeric mixture, with controlled penetration of the graphene nanoplatelets into the fiber sheets. A plurality of dry fiber sheets sprayed with the suspension of graphene nanoplatelets is superimposed. An unpolymerized thermosetting synthetic resin is infused into a lay-up made of the first, second and third blocks. Afterwards, the thermosetting resin is polymerized.

Embodiments described herein can include a composition comprising a thermoset resin with a plurality of graphene flakes dispersed therein, each of the plurality of graphene flakes having a lateral dimension and a thickness. The composition further comprises a reinforcement material dispersed in the thermoset resin. At least about 90% of the plurality of graphene flakes are oriented such that the lateral dimension is within about 10 degrees of a parallel alignment with a horizontal plane. In some embodiments, at least about 95%, or at least about 99% of the plurality of graphene flakes are oriented such that the lateral dimension is within about 10 degrees of a parallel alignment with the horizontal plane. In some embodiments, the reinforcement material can include at least one of a plurality of fibers or a plurality of beads.

A method of manufacturing a composite laminate. The method comprises providing a base layer, providing a discontinuous reinforcing patch on the base layer, and providing a top layer over the base layer and discontinuous reinforcing patch. Also, a composite laminate having a discontinuous reinforcing patch interposed between a base layer and a top layer. The discontinuous reinforcing patch comprises a patterned nanomaterial layer with nanomaterial-filled zones and vacant zones.

A polymer-sheathed multi-filamentary strand for use in braided covers for wiring harnesses intended for use in challenging embodiments comprises a core of glass filaments wrapped in an aramid yarn, and sheathed in a siloxane-modified polyetherimide polymer. Shielding against electromagnetic interference may also be provided.

A composite product substantially reduced the impact force imposed by hard impactor which travelled at the speed in the range of 400 m/s to 1400 m/s simultaneously damping the vibrations and shocks appeared therein is disclosed. At the same time it is light weight with the weight lower than that of 22 to 38 kg/m2and is flexible to adopt the shape suitable for the end applications. A method of manufacturing the composite product of the invention is also disclosed.

A manufacturing method of a highly flameproof laminated composite material is provided in the present disclosure. The manufacturing method of the highly flameproof laminated composite material includes the steps as follows. A raw material is provided, a shaping step is performed and a combining step is performed. The raw material includes an inorganic powder and a polymer material. In the shaping step, the raw material is made into at least one inorganic layer, an inorganic sheet, a ply of film, or a layer of coating. In the combining step, the inorganic layer is made to be connected to a surface of a substrate, so as to obtain the highly flameproof laminated composite material. A weight ratio of the inorganic powder and the polymer material is 0.01-0.1, and a thickness of the inorganic layer is 0.1 mm-8.0 mm.

Embodiments herein include extruded articles, building components and methods of making the same. In an embodiment, an extruded article is included. The extruded article can include a body member including a first portion comprising a first composition, the first composition comprising a polymer resin. The extruded body member can also include a second portion comprising a second composition different than the first composition. The second composition can include a polymer resin, fibers, and at least one component selected from the group consisting of at least 1% by weight particles and at least 5 phr impact modifier. Other embodiments are also included herein.

A method of fabricating a part out of composite material, includes forming a fiber texture from refractory fibers; placing the texture in a mold having an impregnation chamber including in its bottom portion a part made of porous material, the impregnation chamber being closed in its top portion by a deformable impermeable diaphragm separating the impregnation chamber from a compacting chamber; injecting a slip containing a powder of refractory particles into the impregnation chamber; injecting a compression fluid into the compacting chamber, to force the slip to pass through the texture; draining the liquid of the slip via the porous material part, while retaining the powder of refractory particles inside the texture so as to obtain a fiber preform filled with refractory particles; drying the fiber preform; unmolding the preform; and sintering the refractory particles present in the preform in order to form a refractory matrix in the preform.

A method of fabricating a blade. The blade comprises subassemblies made of thermoplastic composite materials, each subassembly comprising an internal arrangement and at least one external arrangement, each internal arrangement comprising a stack of intermediate layers comprising reinforcing fibers impregnated with a semicrystalline thermoplastic matrix, each external arrangement comprising at least one surface layer comprising reinforcing fibers impregnated with an alloy of a semicrystalline thermoplastic polymer and of an amorphous thermoplastic polymer. An assembly film comprising an amorphous thermoplastic material and a ferromagnetic member is interposed between two surface layers of two distinct subassemblies that are to be assembled together by a method of local heating by induction.

Methods for forming vascular components include providing a composite sacrificial body comprising a first sacrificial material having an outer surface and a second sacrificial material applied to at least a portion of the outer surface, molding a solid substrate around the composite sacrificial body, removing the first sacrificial material by deflagration such that at least a portion of the second sacrificial material remains in the same orientation relative to the substrate as originally molded, and subsequently removing the second sacrificial material by a non-deflagration process to form a vascular component. The second sacrificial material can include a phase change material, a syntactic foam including hollow beads bound together with a polymeric binder or a sintered aggregation of hollow beads, a polymeric foam, a water-soluble resin, or an aerogel. The non-deflagration process can include mechanical pulverization, contacting the second sacrificial material with a solvent or chemical etching agent.