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GUIDE TO COMPOSITES

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GUIDE TO COMPOSITES ( guide-to-composites )

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iii) Tooling needs to be able to withstand the process temperatures involved and core materials need to be able to withstand the process temperatures and pressures. iv) For thicker laminates prepreg plies need to be warm “debulked” during the lay-up process to ensure removal of air from between the plies. Typical Applications: Aircraft structural components (e.g. wings and tail sections), F1 racing cars. 6.9 Prepreg - “Out of Autoclave” Description LowTemperature Curing prepregs are made exactly as conventional autoclave prepregs but have resin chemistries that allow cure to be achieved at temperatures from 60-120°C. For low temperature curing (60°C), the working life of the material may be limited to as little as a week, but for higher temperature catalysis (>80°C) working times can be as long as several months. The flow profiles of the resin systems allow for the use of vacuum bag pressures alone, avoiding the need for autoclaves. Materials Options: Resins: Fibres: Cores: Generally only epoxy. Any. As for conventional prepregs. Any, although standard PVC foam needs special care. Main Advantages: i) All of the advantages ((i)-(iv)) associated with the use of conventional prepregs are incorporated in low-temperature curing prepregs. ii) Cheaper tooling materials, such as wood, can be used due to the lower cure temperatures involved. iii) Large structures can be readily made since only vacuum bag pressure is required, and heating to these lower temperatures can be achieved with simple hot-air circulated ovens, often built in-situ over the component. iv) Conventional foam core materials can be used, providing certain procedures are followed. v) Lower energy cost than autoclave process. vi) Robust process providing a high level of dimension tolerance and repeatability. GTC-6-0417 - 55

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