The present invention relates to a resin composition having high miscibility between internal components, low thermal expansion characteristics, and excellent mechanical properties, and a prepreg and a metal clad laminate formed from the same.

A reinforcing fiber fabric substrate has a binder containing a thermosetting resin [A] and a curing catalyst [B] at a basis weight of 0.1 g/m2-4 g/m2 on at least the surface of a reinforcing fiber fabric constructed of reinforcing fiber strands, wherein the reinforcing fiber fabric substrate has a heating temperature (T) in the 80-180 C. range, and the adhesive strength becomes 0.5 N/25 mm or higher at the heating temperature (T) between preform layers molded by laminating this reinforcing fiber fabric substrate at the heating temperature (T).

The present invention provides a siloxane-modified cyclotriphosphazene halogen-free flame retardant, and a preparation method and a use thereof. The siloxane-modified cyclotriphosphazene halogen-free flame retardant has the structural formula as shown in Formula I. In the siloxane-modified cyclotriphosphazene halogen-free flame retardant of the present invention, three kinds of structures of siloxane, aryl phosphorus oxygen compound and cyclotriphosphazene are built in one molecular formula, which combines the advantages of three structures, improves the compatibility between the flame retardant and resins, has a high flame retardant efficiency and a better char formation and can greatly increase the flame retardancy and stability of resin cured products.

A laminar pre-preg of fibre-reinforced curable composite material. The pre-preg includes at least one layer of reinforcing fibres impregnated with a curable resin containing one or more curable thermosetting resin(s) and at least one liquid curative, wherein the curable resin exhibits a cure conversion of at least 95% when cured at a cure temperature in the range of from about 100? C. to about 160? C. and the cure cycle has a duration of no more than 10 minutes, and the glass transition temperature (Tg) of the curable resin when cured is in the range of from about 130? C. to about 165? C.

Pre-impregnated composite material (prepreg) that can be cured/molded to form aerospace composite parts that are designed to tolerate hot and wet conditions. The prepreg includes fibers and an uncured resin. The uncured resin includes an epoxy component that is a combination of a trifunctional epoxy resin, a tetra functional epoxy resin and a solid epoxy resin. The resin includes polyethersulfone and a thermoplastic particle component. The uncured resin also includes a curing agent.

To provide an epoxy-resin composition and prepreg for producing a fiber-reinforced composite material which exhibits excellent curability and has excellent flame retardance and heat resistance, as well as to provide fiber-reinforced composite materials produced using the prepreg and to provide housing for electronic/electrical devices. The epoxy resin composition contains component (A): a phosphorus compound; component (B): an epoxy resin which has at least three epoxy groups in the molecule, and which does not correspond to component (A) nor include component (A); component (C): an epoxy resin curing agent which does not have a urea structure in the molecule; and component (D): a dimethylurea compound represented by formula (a) (in formula (a), R is a hydrogen atom or an alkyl group having any number of 1 to 10 carbons). ##STR00001##

Varnish compositions and prepregs and laminates made therefrom wherein the varnish compositions include at least one first epoxy resin and at least one second epoxy resin that includes a bisphenol-A novolac epoxy resin and a harder wherein the at least one first epoxy resin and the at least one second bisphenol-A novolac epoxy resin are present in the varnish at a weight ratio ranging from about 1:1 to about 1:3.

The present invention is a quartz glass fiber-containing prepreg including: (A) a quartz glass fiber; and (B) a curable resin composition, wherein at least one condition of conditions: (1) a dose of -ray contained in the quartz glass fiber is 0.005 c/cm.sup.2.Math.hour or smaller, and, each of metal ion contents of Na.sup.+, Li.sup.+ and K.sup.+ is 1 ppm or lower; (2) the quartz glass fiber contains the number of foams of 10 foams/m.sup.2 or smaller a unit area; and (3) the quartz glass fiber-containing prepreg has the common bending stiffness in the range of a thickness of 100 to 200 m measured by a method described in JIS R 3420:2013 of 500 N.Math.m.sup.2 or larger is satisfied. This provides a quartz glass fiber-containing prepreg that has particularly excellent dielectric characteristics, has excellent dielectric characteristics and the heat resistance, and/or has high handling property because of high bending stiffness characteristics.

A masterbatch composition suitable for use as a flame retardant in extruded polymer foams, and process for manufacturing the same, and extruded foams containing same; the composition comprising: (a) 20 to 40 parts by weight base resin comprising styrene homopolymer or copolymer; (b) 1 to 16 parts by weight acid scavenger comprising an epoxy-based compound; (c) 2 to 6 parts by weight antioxidant comprising an alkyl or aryl phosphite; and (d) 45 to 60 parts by weight flame retardant comprising a non-hexabromocyclododecane(HBCD) brominated polymer or copolymer, wherein the amounts of (a), (b), (c), and (d) total 100 parts by weight; and (e) 0.6 to 10 parts by weight of pH moderator, based on 100 parts of (a) base resin plus (e) water soluble pH moderator.

A prepreg, including: a fiber layer containing unidirectionally arranged discontinuous carbon fibers and a thermosetting resin; and a resin layer existing on at least one side of said fiber layer and containing a thermosetting resin and a thermoplastic resin; in which said prepreg contains carbon fibers having an areal weight of fibers of 120 to 300 g/m.sup.2, and has a mass fraction of resin of 25 to 50% with respect to the whole mass of said prepreg; and in which a temperature at which a coefficient of interlayer friction is 0.05 or less is in a temperature range of from 40 to 80 C., the interlayer friction being caused at the contact interface between layers of said prepreg when the middle one of three layers that are each made of said prepreg and laid up is pulled out, said coefficient of interlayer friction being measured at 10 C. intervals in a temperature range of from 40 to 80 C. under conditions including a pulling speed of 0.2 mm/min, a perpendicular stress of 0.08 MPa, and a pulling length of 1 mm. There is provided a prepreg with which a wrinkle-free preform can be produced and which expresses excellent, mechanical property in carbon fiber reinforced plastics made thereof.