A multilayer ceramic capacitor includes a ceramic body including a dielectric layer, a first surface and a second surface opposing each other, a third surface and a fourth surface connecting the first surface and the second surface, respectively; internal electrodes disposed inside the ceramic body and exposed to the first and second surfaces, and having one ends exposed to the third surface or the fourth surface; a first side margin portion and a second side margin portion disposed on sides of the internal electrodes exposed to the first and second surfaces; and adhesive layers disposed between the first surface of the ceramic body and the first side margin portion and between the first surface of the ceramic body and the second side margin portion, respectively. An average thickness of each of the first and second side margin portions is 2 m or more and 10 m or less.

A multilayer ceramic capacitor includes a ceramic body including a dielectric layer, a first surface and a second surface opposing each other, a third surface and a fourth surface connecting the first surface and the second surface, respectively; internal electrodes disposed inside the ceramic body and exposed to the first and second surfaces, and having one ends exposed to the third surface or the fourth surface; a first side margin portion and a second side margin portion disposed on sides of the internal electrodes exposed to the first and second surfaces; and adhesive layers disposed between the first surface of the ceramic body and the first side margin portion and between the first surface of the ceramic body and the second side margin portion, respectively. An average thickness of each of the first and second side margin portions is 2 m or more and 10 m or less.

A honeycomb structure including prismatic columnar honeycomb segments and a bonding layer, wherein the bonding layer has rows in each of which bonding layer portions each disposed between two honeycomb segments arranged to face each other are arranged to extend from one point of a peripheral edge of a bonded body of the honeycomb segments to the other point thereof, in a cross section, the bonding layer of each of the-rows is disposed so that among the bonding layer portions arranged in one direction, an outermost circumference bonding layer portion and at least one of the other bonding layer portions are not superimposed on each other on an extension line of the one direction, and a ratio of shift of side surfaces of adjacent honeycomb segments to a length of one side of a side surface of honeycomb segments having the same cross-sectional shape is 10% or less.

A composite body of the present invention includes a base and an oxide layer arranged on the base, the oxide layer containing more than 45% by volume of a perovskite-type oxide phase. The composite body may include a first member, a second member, and a joining portion that joins the first member and the second member, at least one of the first member and the second member serving as the base, and the joining portion serving as the oxide layer. The composite body may include the base and a covering portion that covers the whole or part of a surface of the base, the covering portion being formed of the oxide layer.

The present invention relates to a body (2) provided on air vehicles; at least one transition metal alloy (3) which is located on the body (2) and consists of two-dimensional inorganic compounds by bonding a plurality of carbon atoms (C) and a plurality of nitrogen atoms (N); a plurality of layers (4) containing the transition metal alloy (3); at least one barrier coating (5) consisting of layers (4), which, thanks to the conductivity of the layer (4), prevents and provides protection against plastic and/or elastic deformations that may occur on the body (2) as a result electromagnetic wave that will act on the body (2), thanks to the conductivity of the layer (4).

Methods for repairing composite component voids are provided. For example, one method comprises locating a void in a composite component and subjecting the composite component to a process for repair. The process for repair includes creating a flow path through the void, applying a filler material to the composite component at the flow path, and processing the composite component having the filler material. In some embodiments, the flow path has a first opening on a first side of the composite component and a second opening on a second, opposite side of the composite component. In other embodiments, at least one portion of the flow path extends at a first angle with respect to a lateral direction defined by the CMC component, and at least another portion extends at a second angle with respect to the lateral direction.

A crucible includes an outer element and an inner element. The outer element includes a first portion that is horizontal at a bottom end of the crucible and a second portion that ascends radially outwardly from the bottom end of the crucible to a top end of the crucible at a first acute angle to a vertical axis. The inner element includes a conus with a cylinder at a base of the conus. The conus descends radially outwardly from the top end of the crucible to the bottom end of the crucible at a second acute angle to the vertical axis. The inner element includes a base portion of the cylinder attached to the first portion of the outer element using a sealant to form a hollow mold between an inner portion of the outer element and an outer portion of the inner element.

The invention relates to the use of Dispersion Ceramic Micro-Encapsulated (DCM) nuclear fuel as a meltdown-proof, accident-tolerant fuel to replace uranium dioxide fuel in existing light water reactors (LWRs). The safety qualities of the DCM fuel are obtained by the combination of three strong barriers to fission product release (ceramic coatings around the fuel kernels), highly dense inert ceramic matrix around the coated fuel particles and metallic or ceramic cladding around the fuel pellets.

A method of bonding includes applying a glass composition to at least a first material surface. The glass composition includes a glass powder and a solvent. The first material surface is disposed onto a second material surface. An elevated temperature is applied to the first material surface and the second material surface to form a bond between the first material surface and the second material surface. The first material surface and the second material surface are compressed under an isostatic pressure.

A ceramic matrix composite component and a ceramic insert, and a method for producing the same. The ceramic matrix composite component may include an exterior surface comprising silicon fibers in a silicon carbide matrix. The insert may include a continuous porosity bonded to the exterior surface of the ceramic matrix composite component. The silicon carbide matrix of the ceramic matrix composite component may extend into the porosity of the ceramic insert to bond the ceramic insert to the ceramic matrix composite component.