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2015-10-12 08:00:00

Application of Carbon Fiber Composite Materials in High-tech Field

Due to its unique and outstanding performance, carbon fiber composite materials are widely used in aviation pilots, especially aircraft manufacturing.

Due to its unique and outstanding performance, carbon fiber composite materials are widely used in aviation pilots, especially aircraft manufacturing. Statistics show that at present, the use of carbon fiber composite materials in small business jets and helicopters accounts for 70% to 80%, 30% to 40% on military aircraft, and 15% to 50% on large passenger aircraft. The AV-8B retrofitted "Chang" type aircraft is the most used type of composite material in US military aircraft. Its graphite wings and front fuselage have large graphite epoxy parts. The weight of carbon fiber used in the aircraft accounts for about the total number of aircraft structures. The weight of 26%, so that the whole machine weight loss of 9%, payload than AV-8A aircraft doubled. The data shows that the front fuselage section with a composite material structure can reduce the mass by 32.24% compared with the metal structure. The structural weight coefficient of the fourth-generation military aircraft in foreign countries has reached 27-28% as measured by the structural weight coefficient, an important indicator of military aircraft tactical technical performance. In the future, the proportion of the use of composite materials for the background of the F-22 will be about 35%, of which the carbon fiber composite will become the main material. In the France Telecom 1 communication satellite body structure, the center bearing cylinder with 4 annular stiffeners is made of CFRP, which is connected by screwing on the instrument platform made of CFRP. The satellite skin is made of T300 CFRP. Due to the high specific modulus of CFRP, the M40JB CFRP was used in the 500 mm thrust cylinder, instrument support, 8 support rods, and spacer rings inside the JERS-1 Earth Resources satellite housing in Japan. In addition, the outer shell of the satellite, some The instrument's mounting plate has a carbon fiber/epoxy honeycomb sandwich structure. In 1997, under the support of the National Missile Defense System Test Project (BMDO CEP), the U.S. Air Force Laboratory successfully designed and manufactured an AGS cowl with CFRP reinforcement, weighing only 37 kg. The same type of aluminum alloy protective cover weighed 97 kg. The use of fiber winding technology to achieve automated production, process cycle shortened by 88%, compared to the same type of honeycomb sandwich structure manufacturing composite cowl weight loss 40%, cost reduction of 20%.

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