A porous composite material capable of generating an arc in a microwave field includes an inorganic porous framework and a carbon material loaded on the inorganic porous framework. The average pore size of the inorganic porous framework is 0.2-1000 μm. The porous composite material has an excellent mechanical performance, can generate an arc in a microwave field to quickly generate a high temperature, and thus can be used in fields such as microwave high-temperature heating, biomass pyrolysis, vegetable oil treatment, waste polymer material pyrolysis, petrochemical pyrolysis, carbon-fiber composite material recovery, waste treatment, VOC waste gas treatment, COD wastewater treatment, high-temperature catalysis, waste circuit board full-component recycling, and hydrogen preparation.

The present disclosure relates to a carbon-based porous material microscopically exhibiting a three-dimensional cross-linked net-like hierarchical pore structures with micropores nested in mesopores that are in turn nested in macropores. Such material provides for accelerated adsorption and desorption rates and lower desorption temperatures for recovery of organic gas molecules.

The present disclosure relates to a carbon-based porous material microscopically exhibiting a three-dimensional cross-linked net-like hierarchical pore structures with micropores nested in mesopores that are in turn nested in macropores. Such material provides for accelerated adsorption and desorption rates and lower desorption temperatures for recovery of organic gas molecules.

A system and method of melt infiltrating components is provided. In one example aspect, an inductive heating system includes a heating source that inductively heats a susceptor. The susceptor defines a working chamber in which components can be received. During melt infiltration, the system can heat the susceptor and thus the components and melt infiltrants disposed within the working chamber at a first heating rate. The first heating rate can be faster than 50° C./minute. The system can then heat the components and melt infiltrants at a second heating rate. The first heating rate is faster than the second heating rate. Thereafter, the system can heat the components and infiltrants at a third heating rate. The third heating rate can be a constant rate at or above the melting point of the melt infiltrants. The infiltrants can melt and thus infiltrate into the component to densify the component.

A system and method of melt infiltrating components is provided. In one example aspect, an inductive heating system includes a heating source that inductively heats a susceptor. The susceptor defines a working chamber in which components can be received. During melt infiltration, the system can heat the susceptor and thus the components and melt infiltrants disposed within the working chamber at a first heating rate. The first heating rate can be faster than 50° C./minute. The system can then heat the components and melt infiltrants at a second heating rate. The first heating rate is faster than the second heating rate. Thereafter, the system can heat the components and infiltrants at a third heating rate. The third heating rate can be a constant rate at or above the melting point of the melt infiltrants. The infiltrants can melt and thus infiltrate into the component to densify the component.

A method of pitch infiltration of a densified preform may comprise disposing a pitch on a densified preform surface; heating the pitch and making the pitch into an anisotropic network structure; guiding the pitch through the densified preform in a predetermined direction; aligning the pitch in a predetermined orientation; and stabilizing the pitch. The method may result in a carbon/carbon part having increase wear life, enhanced oxidation protection, and/or reduced moisture sensitivity.

A method of pitch infiltration of a densified preform may comprise disposing a pitch on a densified preform surface; heating the pitch and making the pitch into an anisotropic network structure; guiding the pitch through the densified preform in a predetermined direction; aligning the pitch in a predetermined orientation; and stabilizing the pitch. The method may result in a carbon/carbon part having increase wear life, enhanced oxidation protection, and/or reduced moisture sensitivity.

A thermally-insulating composite material with co-shrinkage in the form of an insulating material formed by the inclusion of microballoons in a matrix material such that the microballoons and the matrix material exhibit co-shrinkage upon processing. The thermally-insulating composite material can be formed by a variety of microballoon-matrix material combinations such as polymer microballoons in a preceramic matrix material. The matrix materials generally contain fine rigid fillers.

A thermally-insulating composite material with co-shrinkage in the form of an insulating material formed by the inclusion of microballoons in a matrix material such that the microballoons and the matrix material exhibit co-shrinkage upon processing. The thermally-insulating composite material can be formed by a variety of microballoon-matrix material combinations such as polymer microballoons in a preceramic matrix material. The matrix materials generally contain fine rigid fillers.

An aerospace mirror having a reaction bonded (RB) silicon carbide (SiC) mirror substrate, and a SiC cladding on the RB SiC mirror substrate forming an optical surface on a front side of the aerospace mirror. A method for manufacturing an aerospace mirror comprising obtaining a green mirror preform comprising porous carbon, silicon carbide (SiC), or both, the green mirror preform defining a front side of the aerospace mirror and a back side of the aerospace mirror opposite the front side; removing material from the green mirror preform to form support ribs on the back side; infiltrating the green mirror preform with silicon to create a reaction bonded (RB) SiC mirror substrate from the green mirror preform; forming a mounting interface surface on the back side of the aerospace mirror from the RB SiC mirror substrate, and forming a reflector surface of the RB SiC mirror substrate on the front side of the aerospace mirror. Additionally, the method can comprise cladding the reflector surface of the RB SiC mirror substrate with SiC to form an optical surface of the aerospace mirror.