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These prepreg materials have been developed using the Cytec resin system 5250-4 and include carbon and glass fibers. The resin is a 350° to 400°F (177° to 204°C) curing bismaleimide resin with a service temperature range of -75° to 400°F (-59° to 204°C).
Carbon fiber prepreg is available in unidirectional tape, woven broadgoods, and roving.

CYCOM 5250-4 is specifically formulated for use in primary aircraft structures. Applications may include engine nacelles, fuselage skin and stiffeners, wing and stabilizer spars and skins, and other critical load-bearing components.

In addition, a variety of secondary structural components may now take advantage of increased performance using high-strain carbon fibers and the improved damage-resistance these composites provide. Glass fiber is available in unidirectional, woven and roving forms. This material is an ideal candidate for application in fighter aircraft, space vehicles and jet engines.

Features and Benefits

• Maximum continuous service temperature up to 400°F (204°C)
• Short-term service temperature up to 450°F (232°C)
• Superior hot/wet properties at 220° to 375°F (104° to 190°C)
• Excellent toughness
• Void-free laminates
• High temperature resistance
• Low thermal conductivity
• Versatile cure
• Excellent compression strength properties after impact
• Shop life greater than 28 days at room temperature
• Fluids / solvent resistant