Provided herein are polymer matrix composites, articles including the polymer matrix composites, and methods of forming the polymer matrix composites. The polymer matrix composite includes a stitched composite and a hybrid barrier layer incorporated within the stitched composite, the hybrid barrier layer including a thin ply and a nanographene dispersed resin. The article includes a high-pressure composite cryogenic tank including the polymer matrix composite. The method includes positioning a dry thin ply between composite plies, stitching the composite plies to form a stitched preform, dispersing nanographene into the resin, and infusing the stitched preform with the modified resin.

A non-compliant fiber-reinforced medical balloon comprises a first fiber layer and a second fiber layer embedded in a continuous matrix of thermally-weldable polymer material defining a barrel wall, cone walls and neck walls. The fibers of the first fiber layer run substantially parallel to one another and substantially parallel to the longitudinal axis. The fibers of the first fiber layer have a pattern of different lengths and are divisible into a first group and a second group based on length.

The present invention is a method of producing a coating liquid-impregnated reinforcing fiber fabric 1b, including allowing a reinforcing fiber fabric 1a to pass substantially vertically downward through the inside of a coating section 20 storing a coating liquid 2 to provide the reinforcing fiber fabric 1a with the coating liquid 2; wherein the coating section 20 includes a liquid pool and a narrowed section which are in communication with each other; wherein the liquid pool has a portion whose cross-sectional area decreases continuously along a running direction of the reinforcing fiber fabric 1a, wherein the narrowed section has a slit-like cross-section and has a smaller cross-sectional area than the top side of the liquid pool, and wherein the vertical height of the portion whose cross-sectional area decreases continuously in the liquid pool is 10 mm or more.

A process for producing a component for an aircraft for the frame, e.g. formers and stringers. Aircraft are being increasingly constructed of polymeric fiber composite to reduce weight. Here, fiber composites were originally composed of thermoset polymer and carbon fibers. Thermoplastic fiber composites are increasingly a research focus. An example is poly(ether ether ketone). However, production of components of thermoplastic fiber composites is complex. An improved process for producing such components includes producing a sheet-like object with a thermoplastic fiber composite having a thermoplastic polymer material and reinforcing fibers embedded therein, forming the sheet-like object for a semifinished part, and solidification of the semifinished part to give the component. Components obtainable by this process are also disclosed.

Provided is a composite laminate having excellent releasability from a mold during a production process, excellent surface appearance (surface smoothness) and mechano-physical properties, and excellent workability and coating adhesion. A composite laminate 1 includes an A layer 2 and a B layer 3, wherein the A layer 2 is provided directly or indirectly on one or both sides of the B layer 3, the A layer 2 contains reinforcing fibers (a1) with an average fiber length of 1 μm to 300 μm, spherical particles (a11) with a volume mean particle diameter of 0.01 μm to 100 μm, and a thermoplastic resin (a2), and the B layer 3 contains reinforcing fibers (b1) with an average fiber length of 1 mm or more and a thermoplastic resin (b2).

An object of the present invention is to provide a prepreg and a laminate for producing a laminate suitable as a structural material, which have excellent joining strength and can be firmly integrated with another structural member by welding. The present invention provides a prepreg including the following structural components: [A] reinforcing fibers, [B] a thermosetting resin, and [C] a thermoplastic resin, wherein [A] has a surface free energy, measured by a Wilhelmy method, of 10 to 50 mJ/m.sup.2, [C] is present on a surface of the prepreg, and the reinforcing fibers [A] are present, which are included in a resin area including [B] and a resin area including [C] across an interface between the two resin areas.

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.

One aspect of the present invention is a composite including: a porous boron nitride sintered body; and a resin filled in pores of the boron nitride sintered body, wherein the boron nitride sintered body has an average pore diameter of 3.5 μm or less.

A method for producing a fiber-reinforced plastic combined body from a prepreg, includes: heating the prepreg in an atmosphere above a room temperature and lower than a curing temperature of the prepreg; provisionally combining pre-products obtained by the heating together or with another component; and retaining and curing the combined pre-products at the curing temperature or higher.

Described herein are composites produced with a barrier ply. The barrier-ply prevents excessive mixing between conventional composite precursors and stoichiometrically-offset precursors during a cure process by gelling early in the cure cycle before extensive mixing can occur. Excess mixing requires the use of thicker offset resin layers with a large stoichiometric offset, which may limit the performance of unitized structures. The use of the barrier plies described herein address this issue and improves the mechanical properties of the final composite product as well as the efficiency for making the composites.