高导C/C材料在疏导式热防护中的应用探索

针对高超声速飞行器飞行时气动加热严重的问题，为了保证高升阻比外形，提出疏导式热防护结构，建立了一套内置高导C/C材料的疏导式热防护结构原理模型，通过数值模拟和电弧风洞的方法对疏导式热防护结构进行了分析，得到内置高导C/C材料的防热效果．数值模拟结果表明来流马赫数为8时，模型驻点温度下降了500度，柱面最低升高了380度，实现了热流从高温区到低温区的疏导，减弱了端头的热载荷，强化了端头的热防护能力．通过电弧风洞试验可以获得相似的结果，内置普通C/C材料表层抗氧化层出现严重烧蚀，而内置高导C/C材料基本不变，验证了数值模拟方法的准确性以及内置高导C/C材料疏导式热防护结构的有效性．

Research on Application of High-Conductivity C/C Materials in Dredged Thermal Protection

In view of the serious aerodynamic heating of hypersonic vehicle in flight, in order to ensure the shape of high lift-drag ratio, a kind of dredged thermal protection structure is proposed. A set of principle model of dredged thermal protection structure with built-in high conductivity C/C material is established. The dredged thermal protection structure is analyzed by numerical simulation and arc wind tunnel, and the heat protection effect is obtained. The numerical simulation results show that when the Mach number is 8, the stationary temperature of the model decreases by 500 degrees, and the temperature on the cylinder surface rises by at least 380 degrees. The heat flow can be dredged from the high temperature zone to the low temperature zone, leading to a reduction of the thermal load exerted on the head. In this way, the thermal protection ability of the head is strengthened. Similar results can be obtained by arc wind tunnel test. The surface oxidation layer of built-in C/C material is severely ablated, while the built-in high conductivity C/C material is almost unchanged. The accuracy of numerical simulation method and the effectiveness of the dredged thermal protection structure with built-in high conductivity C/C material are verified.