Provided are: chopped carbon fiber bundles which have high fluidity without decreasing the dispersibility of carbon fibers and the physical properties of a molded product; and a method for producing chopped carbon fiber bundles with high productivity. Chopped carbon fiber bundles, each of which contain a carbon fiber bundle having a total fineness of from 25,000 dtex to 45,000 dtex (inclusive) and a sizing agent in an amount of from 1% by mass to 5% by mass (inclusive) relative to the total mass of the chopped carbon fiber bundle. The length (L) of each chopped carbon fiber bundle along the fiber direction of the carbon fiber bundle is from 1 mm to 50 mm (inclusive); the ratio of the longest diameter (Dmax) to the shortest diameter (Dmin) of a cross section perpendicular to the fiber direction of each chopped carbon fiber bundle, namely Dmax/Dmin is from 6.0 to 18.0 (inclusive); and the orientation parameter of the single fibers present in the surface of each chopped carbon fiber bundle is 4.0 or less.

Provided are: chopped carbon fiber bundles which have high fluidity without decreasing the dispersibility of carbon fibers and the physical properties of a molded product; and a method for producing chopped carbon fiber bundles with high productivity. Chopped carbon fiber bundles, each of which contain a carbon fiber bundle having a total fineness of from 25,000 dtex to 45,000 dtex (inclusive) and a sizing agent in an amount of from 1% by mass to 5% by mass (inclusive) relative to the total mass of the chopped carbon fiber bundle. The length (L) of each chopped carbon fiber bundle along the fiber direction of the carbon fiber bundle is from 1 mm to 50 mm (inclusive); the ratio of the longest diameter (Dmax) to the shortest diameter (Dmin) of a cross section perpendicular to the fiber direction of each chopped carbon fiber bundle, namely Dmax/Dmin is from 6.0 to 18.0 (inclusive); and the orientation parameter of the single fibers present in the surface of each chopped carbon fiber bundle is 4.0 or less.

Disclosed is a method for manufacturing a polyester fabric for an airbag that can not only prevent or minimize the separation of a sizing agent, which is provided to a yarn through a sizing process, during a weaving process, but can also maximize a peel strength between a textile substrate and a coating layer to be subsequently formed thereon and lower the stiffness of an airbag fabric by effectively removing the sizing agent from the textile substrate after the weaving process is completed. The method of the present invention comprises: applying a polyester-based sizing agent to a polyester yarn; manufacturing a textile substrate with the sizing agent-applied polyester yarn; removing the sizing agent from the textile substrate under an alkaline condition of pH 8 to 10; and forming a coating layer on the sizing agent-removed textile substrate in order to enhance air-tightness.

Disclosed is a method for manufacturing a polyester fabric for an airbag that can not only prevent or minimize the separation of a sizing agent, which is provided to a yarn through a sizing process, during a weaving process, but can also maximize a peel strength between a textile substrate and a coating layer to be subsequently formed thereon and lower the stiffness of an airbag fabric by effectively removing the sizing agent from the textile substrate after the weaving process is completed. The method of the present invention comprises: applying a polyester-based sizing agent to a polyester yarn; manufacturing a textile substrate with the sizing agent-applied polyester yarn; removing the sizing agent from the textile substrate under an alkaline condition of pH 8 to 10; and forming a coating layer on the sizing agent-removed textile substrate in order to enhance air-tightness.

A carbon fiber washer is provided and includes a carbon fiber fabric made of a plurality of fiber bundles being woven, in which each of the plurality of fiber bundles is made of discontinuous fibers; the advantage of the carbon fiber washer of the present invention includes high temperature and fatigue resisting, and weather proofing. The structure of the carbon fiber washer is stable due to the use of discontinuous fibers; breakages of discontinuous fibers do not affect other unbroken discontinuous fibers, so that the structure of the carbon fiber washer would not be loosened or delaminated and the service life can be prolonged accordingly.

The present invention relates to an aqueous, solids-containing dipping bath composition for treating reinforcing inserts for rubber products comprising the following components or consisting of these components, (A) at least one blocked MDI mixture, the MDI mixture comprising MDI oligomers of formula (I), n being a whole number from 1 to 8, and MDI monomers; (B) at least one latex; (C) at least one compound selected from the group consisting of polyacrylates, lignin derivatives and mixtures hereof; and (D) possibly at least one additive; the dipping bath composition being essentially free of epoxides, and the dipping bath composition being essentially free of resorcinol, formaldehyde and the reaction products thereof. ##STR00001##

In order to provide a fabric and a fiber product, which have hygroscopicity and durability as well as flame retardancy, a hydrophilizing agent is added to a fabric containing aramid fibers.

In order to provide a fabric and a fiber product, which have hygroscopicity and durability as well as flame retardancy, a hydrophilizing agent is added to a fabric containing aramid fibers.

The present invention relates to sandwich panels used as aircraft interior parts. In addition to provide a finishing function, the sandwich panels need to have certain mechanical properties and have sufficient fire resistance to retard the spread of fire within the vehicle interior. The present invention provides an aircraft interior panel with skins comprising natural fiber reinforced composites based either on an inorganic thermoset resin or a thermoplastic resin. Such panels provide the required flame and heat resistance, allow easy recycling and disposal, are cheaper and offer significant weight savings over conventional sandwich panels.

The present invention relates to sandwich panels used as aircraft interior parts. In addition to provide a finishing function, the sandwich panels need to have certain mechanical properties and have sufficient fire resistance to retard the spread of fire within the vehicle interior. The present invention provides an aircraft interior panel with skins comprising natural fiber reinforced composites based either on an inorganic thermoset resin or a thermoplastic resin. Such panels provide the required flame and heat resistance, allow easy recycling and disposal, are cheaper and offer significant weight savings over conventional sandwich panels.