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针对高超声速飞行器工作时头锥恶劣的热环境,为了保证飞行器头锥的尖锐外形,提出疏导式热防护结构,利用内置高导热碳材料结构为飞行器头锥提供热防护.采用流固耦合方法对头锥疏导式防热结构进行了分析,验证了头锥内置高导热碳材料具有较好防热效果,其中来流马赫数(Ma)为9时头锥前缘壁面最高温度下降了21.9%,尾部最低温度升高了15.2%,实现了热流由高温区向低温区的转移,削弱了头锥的热载荷,强化了头锥的热防护能力.本文对外蒙皮结构参数、材料参数以及内部高导热碳材料导热率对头锥热防护性能的影响进行了分析,其中头锥最高温度随着蒙皮材料导热系数的增加而降低到一个稳定值;随着蒙皮材料表面黑度的增加而降低;随着蒙皮厚度的增加而升高;随着高导热碳材料导热系数的增加而呈抛物线下降.
Aiming at the harsh environment of the head cone during the operation of the hypersonic vehicle, in order to ensure the sharp shape of the nose cone of the aircraft, a self-guided heat protection structure is proposed to provide thermal protection for the nose cone of the aircraft with a built-in high thermal conductive carbon material structure. The results showed that the maximum thermal conductivity of carbon in the head cone was reduced by 21.9% when the Mach number was 9, The minimum temperature increased by 15.2%, the heat transfer from the high temperature region to the low temperature region was realized, the thermal load of the head cone was weakened and the thermal protection ability of the head cone was strengthened.This paper analyzed the structural parameters, material parameters and internal high thermal conductivity The influence of thermal conductivity of carbon material on the thermal protection performance of the head cone was analyzed, in which the maximum temperature of the head cone decreased to a stable value with the increase of the thermal conductivity of the skin material, and decreased with the increase of the surface blackness of the skin material. With the increase of the thickness of the skin, the parabolicity decreases with the increase of the thermal conductivity of the highly conductive carbon material.