A carbon/carbon part and processes for making carbon/carbon parts are provided. The process involves forming steps, carbonization steps and densification steps. The forming steps may include needling fibrous layers to form fibers that extend in three directions. Pressure may be applied to a fibrous preform at an elevated temperature to increase the fiber volume ratio of the fibrous preform. The densification steps may include filling the voids or pores of the fibrous preform with a carbon matrix.

A carbon/carbon part and processes for making carbon/carbon parts are provided. The process involves forming steps, carbonization steps and densification steps. The forming steps may include needling fibrous layers to form fibers that extend in three directions. Pressure may be applied to a fibrous preform at an elevated temperature to increase the fiber volume ratio of the fibrous preform. The densification steps may include filling the voids or pores of the fibrous preform with a carbon matrix.

A flexible insulation material may be configured to substantially reduce the amount of radiation transmitted therethrough by incorporating a reflective mat of high temperature fibers that withstand temperatures of at least 500 C. The flexible insulation may be stored and used over temperatures ranging from 270 C. to 5000 C. The mat may have optical properties to produce a transmittance of no more than 5% over a range of temperature from 500 C. to 5000 vC. The mat may include high temperature fibers such as carbon and/or silicon carbide and these fibers may be coupled by a binder in a non-woven fabric. The flexible insulation material may be configured in the Flexible Thermal Protection System of a deployable aerodynamic decelerator or a Hypersonic Inflatable Aerodynamic Decelerator and may be durably flexible.

A flexible insulation material may be configured to substantially reduce the amount of radiation transmitted therethrough by incorporating a reflective mat of high temperature fibers that withstand temperatures of at least 500 C. The flexible insulation may be stored and used over temperatures ranging from 270 C. to 5000 C. The mat may have optical properties to produce a transmittance of no more than 5% over a range of temperature from 500 C. to 5000 vC. The mat may include high temperature fibers such as carbon and/or silicon carbide and these fibers may be coupled by a binder in a non-woven fabric. The flexible insulation material may be configured in the Flexible Thermal Protection System of a deployable aerodynamic decelerator or a Hypersonic Inflatable Aerodynamic Decelerator and may be durably flexible.

Provided is a C/C composite that reduces weight when used in an ion engine grid and makes it possible to achieve high levels of both erosion resistance and machinability. A C/C composite for use in an ion engine grid is formed from a completely spread-type carbon fiber nonwoven fabric, and the carbon fibers constituting the carbon fiber nonwoven fabric are pitch-based carbon fibers.

Provided is a C/C composite that reduces weight when used in an ion engine grid and makes it possible to achieve high levels of both erosion resistance and machinability. A C/C composite for use in an ion engine grid is formed from a completely spread-type carbon fiber nonwoven fabric, and the carbon fibers constituting the carbon fiber nonwoven fabric are pitch-based carbon fibers.

A composite manufacturing method includes the step of drawing a nonwoven fabric formed of continuous fibers through a slurry of discontinuous fibers suspended in a dispersive liquid to yield a fiber-modified interlayer comprising a network of said discontinuous fibers attached to said nonwoven fabric.

A composite manufacturing method includes the step of drawing a nonwoven fabric formed of continuous fibers through a slurry of discontinuous fibers suspended in a dispersive liquid to yield a fiber-modified interlayer comprising a network of said discontinuous fibers attached to said nonwoven fabric.

A composite fiber web having superior heat resistance and sound absorption and including a center layer containing a carbon fiber and a heat-resistant layer, and to a method of manufacturing the same. The method of the present invention can exhibit a fast manufacturing speed through a melt-blowing process that will generate economic benefits. The composite fiber web includes a composite layer and individual layers with various fiber diameters resulting in a superior sound absorption rate. The PET fiber included in the heat-resistant layer of the composite layer is an environmentally friendly material with superior heat resistance due to the inclusion of ultrafine fiber. Also, the composite fiber web has superior strength, conductivity, and electromagnetic shielding and deodorization effects, which allows it to be widely utilized for sound absorption materials and in all application fields thereof.

A composite fiber web having superior heat resistance and sound absorption and including a center layer containing a carbon fiber and a heat-resistant layer, and to a method of manufacturing the same. The method of the present invention can exhibit a fast manufacturing speed through a melt-blowing process that will generate economic benefits. The composite fiber web includes a composite layer and individual layers with various fiber diameters resulting in a superior sound absorption rate. The PET fiber included in the heat-resistant layer of the composite layer is an environmentally friendly material with superior heat resistance due to the inclusion of ultrafine fiber. Also, the composite fiber web has superior strength, conductivity, and electromagnetic shielding and deodorization effects, which allows it to be widely utilized for sound absorption materials and in all application fields thereof.