A fabrication method of a hexagonal boron nitride (h-BN)-based thermally-conductive composite film includes the following steps: S1. attaching an adhesive layer to an h-BN film carried on a carrier film, and separating the h-BN film from the carrier film to obtain a film in which an adhesive layer side is defined as a side A and an h-BN film side is defined as a side B; S2. attaching an adhesive layer to the side B of the film obtained in S1; S3. pasting a high-power graphite film to the side B of a film obtained in S2; S4. attaching an adhesive layer to the side B of a film obtained in S3; and S5. shaping a film obtained in S4 according to a required size. The present fabrication method is conducive to improving the production efficiency or yield rate of a thermally-conductive film product and the product quality.

In a flexible display panel and a flexible display device provided by the present application, a bending end of a support layer is configured inwardly to be shorter than a flexible display module to reduce a bending angle of the support layer. In this way, bending stress on the support layer can be reduced, thereby increasing attachment quality of the support layer and improving attachment reliability.

The purpose of the present invention is to provide a thermal conductor achieving both excellent light weight and excellent rigidity and also having excellent heat dissipation property. In order to achieve the above object, the thermal conductor according to the present invention has the following configuration. That is, a thermal conductor in which a sheet-shaped thermal conductive material (II) having an in-plane thermal conductivity of 300 W/m.Math.K or more is contained in a porous structure (I) configured of reinforcing fibers and a resin.

The present application relates to a composite heat dissipation material. The composite heat dissipation material comprises at least one artificial graphite layer and a graphitic heat dissipation layer. The graphitic heat dissipation layer includes a graphite material layer, and the graphite material layer is not formed from artificial graphite materials. Further, the graphitic heat dissipation layer is bonded to the artificial graphite layer. The composite heat dissipation material of the present application can efficiently and rapidly dissipate heat energy produced from a heating source, thereby lowering temperature thereof.

Robust multi-purpose, multi-layer, building construction tapes and building construction framing members and related wall assemblies are disclosed that comprise a sheet metal framing member (all profiles) in combination with a new and more robust type of multi-layer building construction tape for fire safety and sound reduction. The multi-layer building construction tape comprises a flexible thermal barrier layer attached to (1) a flexible intumescent material layer having a lesser width (thereby enabling flex-lock rollover) and/or (2) a resilient unfoamed cross-linked polyethylene layer. In combination, the thermal barrier layer is on a surface of the sheet metal framing member, whereas the thermal barrier layer is attached to the intumescent layer or polyethylene layer (as the case may be) such that the thermal barrier layer is between the sheet metal framing member and the intumescent layer or the polyethylene layer. The multi-layer building construction tapes disclosed herein slow and impede the spread of fire and smoke (during a fire) and also reduces sound transmission between adjacent rooms in a building.

An optical mirror assembly includes a crystalline face sheet and a carbon fiber sandwich. The crystalline face sheet has a first surface configured to reflect light and a second surface coupled to the carbon fiber sandwich by a layer of epoxy. The carbon fiber sandwich is configured to structurally support the crystalline face sheet. The carbon fiber sandwich includes a first carbon fiber layer, a second carbon fiber layer and a substrate positioned between the first carbon fiber layer and the second carbon fiber layer.

A hybrid metal composite (HMC) structure comprises tiers comprising fiber composite material structures, and additional tiers longitudinally adjacent one or more of the tiers and comprising perforated metallic structures and additional fiber composite material structures laterally adjacent the perforated metallic structures. Methods of forming an HMC structure, and related rocket motors and multi-stage rocket motor assemblies are also disclosed.

The breathable sheet of the present invention is comprised of a 4-methyl-1-pentene-based polymer or a resin composition containing the 4-methyl-1-pentene-based polymer as a main component. In addition, the breathable sheet of the present invention is preferably selected from the group consisting of a net, a mesh, a non-woven fabric, a woven fabric, and a perforated sheet.

Aircraft stringers having carbon fiber reinforced plastic (CFRP) material reinforced flanges are disclosed. An example stringer to be coupled to a skin of an aircraft comprises a flange. The flange includes a first portion of a first stiffening segment. The flange further includes a first portion of a second stiffening segment coupled to the first portion of the first stiffening segment. The flange further includes a CFRP reinforcement segment coupled to the first portion of the first stiffening segment and to the first portion of the second stiffening segment. The CFRP reinforcement segment strengthens the first portion of the first stiffening segment and the first portion of the second stiffening segment.

A laminate structure is disclosed including a fibre laminate impregnated with a laminate matrix material, and a veil of carbon nanotubes impregnated with a veil matrix material. The laminate matrix material and the veil matrix material doped with carbon particles. The veil provides lightning strike protection. The structure is manufactured by co-curing the laminate matrix material and the veil matrix material to bond the veil of carbon nanotubes to the fibre laminate.