Abstract: A thermosetting resin composition contains at least: [A] a thermosetting resin; [B] a curing agent; and [C] polyamide particles satisfying following (c1) to (c6): (c1) a melting point of polyamide resin constituting the polyamide particles is 200 to 300° C.; (c2) a crystallization temperature of the polyamide resin constituting the polyamide particles is 150° C. to 250° C.; (c3) a number average particle size of the polyamide particles is 1 to 100 ?m; (c4) a sphericity of the polyamide particles is 80 to 100; and (c5) the linseed oil absorption of the polyamide particles is 10 to 100 mL/100 g. A thermosetting resin composition of the present invention enables suitable production of a fiber-reinforced composite material having sufficient compressive strength after impact and wet heat compression performance.

Abstract: The present invention addresses the problem of providing a prepreg that yields a carbon fiber composite material that has exceptional tensile strength, heat resistance, and impact resistance and is suitable as a structural material of an aircraft body, wherein the resin composition used in the prepreg furthermore has exceptional viscosity stability, the prepreg containing a resin composition that contains carbon fibers and at least the constituent elements [A]—[D] as defined.

Abstract: The objective of the present invention is to provide a prepreg and a fiber reinforced composite material using this prepreg. This prepreg has good handleability, is suitable for producing a reinforced composite material in a short-time and without using an autoclave, and is capable of yielding a fiber reinforced composite material exhibiting excellent impact resistance, wherein the occurrence of voids has been suppressed. To attain the objective, this prepreg comprises a reinforced fiber [A] that is layered and partially impregnated with an epoxy resin composition containing an epoxy resin [B] and a hardener [C], the impregnation rate ? being 30 to 95%. In this prepreg, a thermoplastic resin [D] insoluble in the epoxy resin [B] is distributed unevenly over a surface on one side of the prepreg, and a portion not impregnated with the epoxy resin composition is localized in the layer of the reinforced fiber [A] on the side where the thermoplastic resin [D] is distributed unevenly.

Abstract: The invention provides a prepreg having high storage stability and serving suitably for producing components, such as structural members and interior members of aircraft and structural members of aircraft engines, that require high heat resistance under high temperature and high humidity conditions, where the prepreg exhibits good physical properties and good combustion properties. The prepreg is produced by impregnating component [A] with an epoxy resin composition containing components [B] to [D], wherein component [A] in the prepreg accounts for 50 mass % or more, where [A] is a carbon fiber, [B] is an epoxy resin, [C] is a fluorene type curing agent having a maximum particle size of 100 ?m or less, and [D] is a thermoplastic resin.

Abstract: Provided is a prepreg including the following constituents [A] to [C], the prepreg satisfying the following conditions [I] to [III]: [A]: a sizing agent-coated carbon fiber; [B]: an epoxy resin having a specific structure; and [C]: a hardener for [B], [I]: an epoxy resin composition including the constituents [B] and [C] has a nematic-isotropic phase transition temperature in a temperature range of 130° C. to 180° C.; [II] a prepreg after isothermal holding at 100° C. for 30 minutes does not have a high-order structure originated from a diffraction angle of 2?=1.0° to 6.0° measured by wide angle X-ray diffraction at 100° C.; and [III]: a prepreg after isothermal holding at 180° C. for 2 hours has a high-order structure originated from the diffraction angle of 2?=1.0° to 6.0° measured by wide angle X-ray diffraction at 180° C.

Abstract: The objective of the present invention is to provide a prepreg and a fiber reinforced composite material using this prepreg. This prepreg has good handleability, is suitable for producing a reinforced composite material in a short-time and without using an autoclave, and is capable of yielding a fiber reinforced composite material exhibiting excellent impact resistance, wherein the occurrence of voids has been suppressed. To attain the objective, this prepreg comprises a reinforced fiber [A] that is layered and partially impregnated with an epoxy resin composition containing an epoxy resin [B] and a hardener [C], the impregnation rate ? being 30 to 95%. In this prepreg, a thermoplastic resin [D] insoluble in the epoxy resin [B] is distributed unevenly over a surface on one side of the prepreg, and a portion not impregnated with the epoxy resin composition is localized in the layer of the reinforced fiber [A] on the side where the thermoplastic resin [D] is distributed unevenly.