An approach to seeker windows for aircraft comprises a window layer comprising an IR transparent material, the window layer comprising a first side and a second side substantially opposite the first side; and a heating layer on the first side or the second side of the window layer, the heating layer configured to apply a heating profile to the window layer to reduce thermal shock imparted to the window layer when the seeker window is exposed to hypersonic flight conditions.

A ceramic joined body (1) includes: a pair of ceramic plates (2,3) that include a conductive material; a conductive layer (4) and an insulating layer (5) that are interposed between the pair of ceramic plates (2, 3); and a pair of intermediate layers (6, 7) that are interposed between the pair of ceramic plates (2, 3) and the conductive layer (4) and are in contact with the pair of ceramic plates (2, 3) and the conductive layer (4).

The present invention discloses an artificial graphite flake manufacturing method, which uses the PI (polyimide) films as the material; via a stacking step, a first heating step and a second heating step, the PI films are processed to form the artificial graphite flakes so as to increase the lubrication and the hardness, improve the heat conduction for balancing temperature increase and better the smoothness; in addition, via a perforation step, a hole structure is formed on the artificial graphite flakes so as to increase the heat diffusion area and the air permeability of the artificial graphite flakes, and then increase the defect-free rate and the smoothness thereof.

An aerospace component may comprise a fiber reinforced composite material. The fiber reinforced composite material includes a plurality of fiber layers and a carbon matrix surrounding the plurality of fiber layers. A plurality of ceramic particles is dispersed in the carbon matrix. A first fiber layer of the plurality of fiber layers may include a carbon fiber, and a second fiber layer of the plurality of fiber layers may include a non-carbon fiber. A hardness of the non-carbon fiber is greater than a hardness of carbon fiber.

A polycrystalline super hard construction has a first region having a body of thermally stable polycrystalline super hard material having a plurality of intergrown grains of super hard material; a second region forming a substrate having a hard phase and a binder phase; and a third region interposed between the first and second regions. The third region includes a composite material having a first phase comprising a plurality of non-intergrown grains of super hard material, and a matrix material. A fourth region interposed between the second and third region has a major proportion having one or more components of the binder material of the second region, and one or more reaction products between the binder material of the second region and one or more components of the third region.

An embodiment of a PCD insert comprises an embodiment of a PCD element joined to a cemented carbide substrate at an interface. The PCD element has internal diamond surfaces defining interstices between them. The PCD element comprises a masked or passivated region and an unmasked or unpassivated region, the unmasked or unpassivated region defining a boundary with the substrate, the boundary being the interface. At least some of the internal diamond surfaces of the masked or passivated region contact a mask or passivation medium, and some or all of the interstices of the masked or passivated region and of the unmasked or unpassivated region are at least partially filled with an infiltrant material.

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.

The present invention discloses a polyimide-based composite carbon film with high thermal conductivity and a preparation method therefor. The preparation method includes: uniformly coating the surface of a polyimide-based carbon film with an aqueous graphene oxide solution, and then covering the same with another polyimide-based carbon film uniformly coated with an aqueous graphene oxide solution; repeating such operation; after the polyimide-based carbon films are dried, bonding the polyimide-based carbon films by means of graphene oxide so as to form a thick film; bonding the polyimide-based carbon films more tightly by means of further low-temperature hot pressing; and finally, obtaining a thick polyimide-based carbon film with high thermal conductivity by repairing defects by means of low-temperature heating pre-reduction and high-temperature and high-pressure thermal treatment. The thick polyimide-based carbon film with high thermal conductivity has a thickness greater than 100 μm and an in-plane thermal conductivity of even reaching 1700 W/mK or above.

A polycrystalline super hard construction is disclosed having a first region comprising a body of thermally stable polycrystalline super hard material having an exposed surface forming a working surface, and a peripheral side edge, the polycrystalline super hard material comprising a plurality of grains of super hard material; a second region forming a substrate to the first region; and a third region interposed between the first and second regions. The third region extends across a surface of the second region along an interface, the interface comprising a portion having an uneven topology and a substantially planar portion, the third region comprising a composite material including a first phase comprising a plurality of non-intergrown diamond grains, and a matrix material.

There is provided a group III nitride laminate, including: a substrate comprised of silicon carbide; a first layer comprised of aluminum nitride and formed on the substrate; a second layer comprised of gallium nitride and formed on the first layer; and a third layer formed on the second layer and comprised of group III nitride having an electron affinity lower than that of the gallium nitride which is comprised in the second layer, the second layer having a thickness of less than 500 nm, the second layer containing iron at a concentration of less than 1×10.sup.17/cm.sup.3, and the second layer containing carbon at a concentration of less than 1×10.sup.17/cm.sup.3.