The present invention provides a pocket fabric, including at least one tubular pocket, where each tubular pocket includes: a tubular sidewall formed between two ends of the tubular pocket; at least two filling chambers formed between the two ends and surrounded by the tubular sidewall; and at least one mesh barrier layer provided between two filling chambers and substantially perpendicular to the tubular sidewall, wherein the filling chambers are communicated with each other. The mesh barrier layer allows fluffy filler to be maintained in the filling chamber and substantially prevents it from moving to adjacent filling chambers, so that the filler cannot accumulate in one place due to gravity or other external forces. Therefore, the pocket fabric of the present invention can maintain the desired warmth retention property after a period of use with filler evenly distributed inside.

Multilayer structure for transporting hydrogen, including, from the inside, at least one sealing layer and at least one composite reinforcing layer, an innermost composite reinforcing layer being wound around an outermost adjacent sealing layer, the sealing layers of a composition predominantly of at least one semi-crystalline, long-chain polyamide thermoplastic polymer P1i (i=1 to n, n being the number of sealing layers), the Tf of which, as measured according to ISO 11357-3: 2013, is greater than 160° C., with the exception of one polyether block amide (PEBA), up to 50% by weight of impact modifier relative to the total weight of the composition and up to 1.5% by weight of plasticiser relative to the total weight of the composition, the composition being free of nucleating agent, and at least one of the composite reinforcing layers being of a fibrous material.

Disclosed is a ceramic matrix component having a fibrous core and a ceramic matrix composite shell surrounding at least a portion of the fibrous core. The ceramic matrix composite shell comprises a fibrous preform. The fibrous core has a greater porosity than the fibrous preform. A method of making the ceramic matrix component is also disclosed.

A method for manufacturing a synthetic non-perforated drainable material is disclosed herein. Generally, the method includes injecting a coating material with air, applying the air-injected coating material to the first side of the material, and curing the air-injected material such that it adheres. Once cured, the material has a highly efficient drainage rate that remains consistent throughout the life of the material.

The present invention has an object of providing a prepreg for producing a laminate suitable as a structural material, and a laminate, which have excellent combustion resistance, compressive strength and interlaminar fractural toughness values, and can be firmly integrated with another structural member by welding. The present invention is a prepreg including structural components: [A] reinforcing fibers, [B] a thermosetting resin, and [C] a thermoplastic resin [C], wherein [B] includes at least one resin selected from a cyanate ester resin having an average cyanate equivalent of 220 or less, a bismaleimide resin having an average maleimide equivalent of 210 or less, and a benzoxazine resin having an average oxazine equivalent of 300 or less, [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.

Systems and techniques to provide a flexible, lightweight material that is also effective at protecting a body from ballistic threats are described. An example composite material described herein is fiber-based, and it includes one or more first regions where the fiber composite material is consolidated, and one or more second regions where the fiber composite material is unconsolidated. Example methods of manufacturing the composite material disclosed herein include using a specialized tool with a heated platen press or an autoclave. The tool may include one or more protrusions and/or cavities that contact a precursor composite material to transform the precursor material into a partially consolidated fiber composite material, which is suitable for use as body armor, among other potential applications for the manufactured composite material.

The present disclosure discloses a fiber structure, including a plurality of fiber layers. The plurality of the fiber layers are stacked and arranged in a surrounding manner and are impregnated and cured in sequence. The fiber structure of the present disclosure is high in structural strength and low in mass. The present disclosure further provides a gymnastic apparatus force bearing frame, including the above-mentioned fiber structure, which is beneficial to reducing the weight of the gymnastic apparatus force bearing frame, facilitating the movement, transportation, disassembling, and assembling of the apparatus, and reducing the labor burden of an operator.

A thermal management system.

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.

Disclosed herein is a method of reinforcing a composite comprising determining a location of a first cooling hole in a plurality of plies; where a cooling gas is transported through the cooling hole; disposing a z-fiber in the plurality of plies at a location proximate to where the first cooling hole will be located; where the z-fiber enters the plurality of plies at either an upper surface or a lower surface; and where the z-fiber traverses a portion of the plurality of plies in the z-direction proximate to the first cooling hole; and traverses the plurality of plies in an x or y direction further away from the first cooling hole; where the z-direction is in the thickness direction of the plurality of plies and where the x and y-direction are perpendicular to the z-direction.