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首页> 外文会议>Proceedings of the 3rd Sino-Italian conference on space aerothermodynamics and hot structures >NEW ADVANCED DESIGN OF CARBON/CARBON COMPOSITES FOR HYPERSONIC SYSTEMS.
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NEW ADVANCED DESIGN OF CARBON/CARBON COMPOSITES FOR HYPERSONIC SYSTEMS.

机译：超音速系统的碳/碳复合材料的新高级设计。

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Hypersonic flight presents a difficult challenge for control design. High velocity causes the aircraft to be very sensitive to changes in the flight condition. For example, at an altitude of 34 km and a Mach number of 15 a 1-deg increase in angle of attack produces a normal acceleration of 3.5 m/s2, a load factor of about l/3g. This is a critical aspect for structures. Thermal loads are also protagonists as one of the critical areas for structures. Carbon/Carbon (C/C) composites, which withstand temperatures in excess of 2000°C without major deformation, are by far the most suitable materials for these applications. Moreover, C/C composites with high thermal conductivity are important for first wall components for nuclear fusion reactors, hypersonic aircraft, missiles and spacecraft, thermal radiator panels and electronic heat sinks. The thermal conductivity at temperatures major of 1000°C increases with the heat treatment temperature, particularly above 2800°C, as more graphitic carbon is associated with a higher thermal conductivity. However, there is one major drawback, which is its susceptibility to oxidation above 500°C which becomes progressively more severe as the temperature rises. The rate of oxidation is limited only by the diffusion rate of oxygen through the surrounding gas to the carbon surface. Another drawback is that the properties are dependent on the manufacturing methods used. Although the general production technology is known, the combination of processes to achieve specially tailored properties remains the expertise of particular manufacturers. For these reasons much research has to be done, in order to optimize each stage of production of these composites.Here are reported the main results of SASLab research on C/C composites production.
机译：高超音速飞行对控制设计提出了艰巨的挑战。高速导致飞机对飞行状态的变化非常敏感。例如，在34 km的高度和15的马赫数下，迎角每增加1度就会产生3.5 m / s2的法向加速度，其载荷系数约为1 / 3g。这是结构的关键方面。热负荷也是结构的关键领域之一。迄今为止，碳/碳（C / C）复合材料可承受超过2000°C的温度而不会发生重大变形，是目前最适合这些应用的材料。此外，具有高导热率的C / C复合材料对于核聚变反应堆，高超音速飞机，导弹和航天器，散热器面板和电子散热器的第一壁组件很重要。主要温度为1000°C时的导热系数会随热处理温度而增加，尤其是在2800°C以上，这是因为石墨碳越多，导热系数就越高。然而，有一个主要缺点，那就是它在500℃以上对氧化的敏感性，随着温度的升高其氧化作用变得越来越严重。氧化速率仅受氧气通过周围气体向碳表面的扩散速率的限制。另一个缺点是性能取决于所使用的制造方法。尽管已知一般的生产技术，但实现特殊定制属性的过程组合仍然是特定制造商的专长。由于这些原因，必须进行大量研究以优化这些复合材料的生产的每个阶段。这里报道了SASLab研究C / C复合材料的主要结果。

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