One aspect of the present invention provides a composite sheet which comprises a nitride sintered body having a porous structure and a semi-cured product of a thermosetting resin composition impregnated into the nitride sintered body, the line roughness Rz specified by JIS B 0601:2013 of at least one main surface being 10 μm or less.

In a ceramic/copper/graphene assembly, a ceramic member, a copper member formed of copper or a copper alloy, and a graphene-containing carbonaceous member containing a graphene aggregate are joined. At a joining interface between the copper member and the graphene-containing carbonaceous member, an active metal carbide layer containing a carbide of one or more kinds of active metals selected from Ti, Zr, Nb, and Hf is formed on a side of the graphene-containing carbonaceous member, and a Mg solid solution layer having Mg dissolved in a matrix phase of Cu is formed between the active metal carbide layer and the copper member.

In a ceramic/copper/graphene assembly, a ceramic member, a copper member formed of copper or a copper alloy, and a graphene-containing carbonaceous member containing a graphene aggregate are joined. At a joining interface between the copper member and the graphene-containing carbonaceous member, an active metal carbide layer containing a carbide of one or more kinds of active metals selected from Ti, Zr, Nb, and Hf is formed on a side of the graphene-containing carbonaceous member, and a Mg solid solution layer having Mg dissolved in a matrix phase of Cu is formed between the active metal carbide layer and the copper member.

A piston for a heavy duty diesel engine including a composite layer forming at least a portion of a combustion surface is provided. The composite layer has a thickness greater than 500 microns and includes a mixture of components typically used to form brake pads, such as a thermoset resin, an insulating component, strengthening fibers, and an impact toughening additive. According to one example, the thermoset resin is a phenolic resin, the insulating component is a ceramic, the strengthening fibers are graphite, and the impact toughening additive is an aramid pulp of fibrillated chopped synthetic fibers. The composite layer also has a thermal conductivity of 0.8 to 5 W/m.Math.K. The body portion of the piston can include an undercut scroll thread to improve mechanical locking of the composite layer. The piston can also include a ceramic insert between the body portion and the composite layer.

A piston for a heavy duty diesel engine including a composite layer forming at least a portion of a combustion surface is provided. The composite layer has a thickness greater than 500 microns and includes a mixture of components typically used to form brake pads, such as a thermoset resin, an insulating component, strengthening fibers, and an impact toughening additive. According to one example, the thermoset resin is a phenolic resin, the insulating component is a ceramic, the strengthening fibers are graphite, and the impact toughening additive is an aramid pulp of fibrillated chopped synthetic fibers. The composite layer also has a thermal conductivity of 0.8 to 5 W/m.Math.K. The body portion of the piston can include an undercut scroll thread to improve mechanical locking of the composite layer. The piston can also include a ceramic insert between the body portion and the composite layer.

Provided are a planographic printing plate precursor including an aluminum support, and an image recording layer and a protective layer which are provided on the aluminum support in this order, in which a thickness of the protective layer is 0.2 μm or greater, and Expression (1) is satisfied in a case where a Bekk smoothness of a surface of an outermost layer on a side opposite to a side where the image recording layer is provided is denoted by b seconds; a planographic printing plate precursor laminate; a plate-making method for a planographic printing plate; and a planographic printing method.

Provided are a planographic printing plate precursor including an aluminum support, and an image recording layer and a protective layer which are provided on the aluminum support in this order, in which a thickness of the protective layer is 0.2 μm or greater, and Expression (1) is satisfied in a case where a Bekk smoothness of a surface of an outermost layer on a side opposite to a side where the image recording layer is provided is denoted by b seconds; a planographic printing plate precursor laminate; a plate-making method for a planographic printing plate; and a planographic printing method.

a film composite for manufacturing a package for planar carriers of pharmaceutical active substances, for example transdermal patches, encompassing, in a direction from the outer side of the film composite toward its inner side: a metal layer; an acrylic-acid-containing joining layer; a polyethylene layer; and a COC layer made of cycloolefin copolymer, a side of the COC layer which faces away from the metal layer being an exposed surface of the film composite, wherein provision is made that the polyethylene layer encompasses metallocene polyethylene.

a film composite for manufacturing a package for planar carriers of pharmaceutical active substances, for example transdermal patches, encompassing, in a direction from the outer side of the film composite toward its inner side: a metal layer; an acrylic-acid-containing joining layer; a polyethylene layer; and a COC layer made of cycloolefin copolymer, a side of the COC layer which faces away from the metal layer being an exposed surface of the film composite, wherein provision is made that the polyethylene layer encompasses metallocene polyethylene.

A thermoplastic surfacer for providing lightning strike protection to a composite component of an aircraft, methods of manufacturing the surfacer, and methods of applying the surfacer to a composite part. The thermoplastic surfacer includes a broadgood having an amorphous thermoplastic resin, one or more fillers embedded into the broadgood, and a lightning strike protection mesh or foil embedded into the broadgood. When applying the surfacer to a composite part of an aircraft, the method includes draping the surfacer on an at least partially unconsolidated composite part, consolidating the at least partially unconsolidated composite part by heating the part to a temperature at or above a melt temperature of a resins used in the part and in the surfacer, and filling at least one surface defect in the consolidated part using the amorphous thermoplastic polymer resin and milled fibers provided in the thermoplastic surfacer.