A vehicle running board includes opposing vertical walls extending along a length of a tubular structure and including a carbon-fiber component. Opposing horizontal walls extend between the opposing vertical walls and include a glass component. The opposing vertical and opposing horizontal walls form the tubular structure having a generally rectilinear cross section. A polymer outer covering extends over the opposing vertical and opposing horizontal walls.

A method for manufacturing a composite pressurized-fluid vessel including winding a first polyolefin resin-based tape thereby forming a first layer of the vessel, depositing an intermediate second layer on the first layer, consisting of a material having variable permeability properties depending on the temperature and permeability below a pre-determined temperature threshold and non-permeability above the temperature threshold, winding a second resin-based tape on the intermediate second layer thereby forming a third layer, and cooling the intermediate second layer to a temperature below the temperature threshold while the first and third layers are each kept at a temperature above the melting temperature of their resin. Wherein the tape forming the third layer is based on a different resin from the first layer and during the step of depositing the intermediate second layer.

In a method for producing a fiber-reinforced resin molded body (10) by heat-compressing fiber substrates (11A to 11D) together with a thermosetting resin (15) so that the thermosetting resin (15) is impregnated into the fiber substrates (11A to 11D) and cured, a thermosetting resin powder (15A) is disposed in contact with at least one surface of the fiber substrates (11A to 11D), the fiber substrates (11A to 11D) are heat-compressed together with the thermosetting resin powder (15A) by a mold (30) so that the thermosetting resin powder (15A) is melted, impregnated into the fiber substrates (11A to 11D), and cured. Also disclosed is a fiber-reinforced resin molded body as well as a vehicle or airframe including a fiber-reinforced resin molded body.

The present invention relates to a compression limiter made of a first thermoplastic composition comprising a semi-crystalline semi-aromatic polyamide. The invention further relates to a process for producing the compression limiter, and to an assembly comprising the compression limiter and a thermoplastic body made of a second thermoplastic polyamide composition. According to the invention, the compression limiter is made of a thermoplastic composition.

The present invention relates to resin compositions, fiber reinforced polymeric structures and electromagnetic induction processes for making same. Such magnetic induction processes are pulsed processes that can be optionally coupled with cooling steps between pulses. The aforementioned fiber reinforced polymeric structures can take forms that include, but are not limited to, pipes; pressure vessels, including rocket motor cases and fire extinguishers; golf club shafts; tennis and badminton racquets; skis; snowboards; hockey sticks; fishing rods; bicycle frames; boat masts; oars; paddles; baseball bats; and softball bats. In addition, such fiber reinforced polymeric structures can be supplemented with other materials, such as a rocket propellant, to form articles, for example, a rocket motor.

A fiber-reinforced resin article with excellent mechanical properties can be provided efficiently in a short time. The method includes 3D printing including forming fibers and a resin by a 3D printer, and pressurizing the 3D printed article formed by the 3D printing step, in which the pressurizing is performed at a temperature at which the resin of the 3D printed article is softened, and heating to the temperature at which the resin is softened is performed by induction heating.

[Object]

The purpose of the present invention is to provide a layered composite that is high in both flexural modulus and moldability.

[Solving Means]

Provided is a layered composite including a carbon-fiber-reinforced resin in which a chopped strand prepreg obtained by impregnating fiber in resin is oriented in such a manner as to exhibit pseudo-isotropic properties, and a steel plate that is layered on at least one surface of the carbon-fiber-reinforced resin and has a tensile breakage elongation ϕ of equal to or more than 20%, the flexural modulus in a flat plate state obtained in compliance with ASTM D-790 being equal to or more than 30 GPa.

The invention relates to a method and facility for manufacturing a tape of reinforcement filaments impregnated by a polymer matrix, as well as a tape produced thereby, said tape having a constant width across the entire length thereof, wherein the filaments extend in a direction parallel to the length of the tape, from a strand of filaments coming from a feeding reel. The method including steps and units that make it possible to manage the unwinding tension of the strand, to guide the strand on the axis of the machine, to manage the width of the strand, to deposit the polymer on the strand by electrostatic powdering, with a polymer weight ratio of around 20% to around 75% to melt the polymer, to calibrate the width and thickness of the tape and to collect the tape on the storage reel.

Embodiments are directed to systems and methods for two or more cured composite assemblies that are bonded together to form a tubular composite structure, wherein each of the cured composite assemblies do not have a tubular shape. The tubular composite structure may form a spar for an aerodynamic component, for example. The two or more cured composite assemblies may comprise carbon or fiberglass composite materials or a combination of materials. Each of the cured composite assemblies may further comprise axial edges that are configured to be bonded to another of the cured composite assemblies, wherein the axial edges have a sloped shape. An adhesive agent may be applied on the axial edges for bonding two cured composite assemblies. Alternatively, or additionally, one or more fasteners may be used to attach the axial edges of at least two cured composite assemblies.

Embodiments are directed to systems and methods for two or more cured composite assemblies that are bonded together to form a tubular composite structure, wherein each of the cured composite assemblies do not have a tubular shape. The tubular composite structure may form a spar for an aerodynamic component, for example. The two or more cured composite assemblies may comprise carbon or fiberglass composite materials or a combination of materials. Each of the cured composite assemblies may further comprise axial edges that are configured to be bonded to another of the cured composite assemblies, wherein the axial edges have a sloped shape. An adhesive agent may be applied on the axial edges for bonding two cured composite assemblies. Alternatively, or additionally, one or more fasteners may be used to attach the axial edges of at least two cured composite assemblies.