飞行器控制舵疏导式组合结构热防护性能试验与数值分析

Experimental and numerical analysis of thermal protection performance for composite conductive structures of aircraft leading edges

中文关键词: 舵/翼前缘  高导热C/C  高温热疏导/热匹配  一体化防热结构  可重复使用

英文关键词: the leading edges of the wing and rudder  high thermal conductivity C/C  high temperature heat conduction / matching  integrated heat protection structure  reusable

中文摘要:

      为适应飞行器舵/翼在临近空间长航程飞行过程中气动维形的需求,以碱金属为工质,将具有高温热疏导能力的钨、钼固溶强化镍基合金疏导装置嵌套在高导热C/C防热罩和碳基柔性高导热夹层内侧。通过仿形石英灯加热器设计,开展了不同飞行环境条件下的地面性能测试试验。结合试验结果利用数值分析方法对其整体传热能力和各工况下的热防护效果进行了分析。结果表明,疏导装置启动时有效导热系数可由18.42 W/(m.K)提升至1390.00 W/(m.K),稳定状态可降低前缘峰值温度21.70%~23.04%,疏导式组合结构表面最大温差降幅64.80%,极大减小由温度梯度产生的热应力,有效提升高温环境下热结构匹配性和材料可靠性,可多次重复使用。该组合式热防护结构是解决高速飞行器前缘等高气动加热区烧蚀防热变形问题行之有效的技术途径之一,可针对新一代飞行器气动外形和飞行环境开展进一步工程应用研究。

英文摘要:

      In order to avoid the problem of aerodynamic ablation of aircraft rudder / wing during long range flight in near space, using alkali metal as working fluid, between the high thermal conductivity C / C heat shield and carbon based flexible high thermal conductivity layer, install a device with high-temperature thermal conduction capability. The tests under different flight environment conditions were carried out by using profiling quartz lamp heater. The overall heat transfer capacity and thermal protection effect are analyzed by numerical analysis method. The results show that the effective thermal conductivity of the dredging device can be increased from 18.42 W/(m.K) to 1330 W/(m.K) when starting, can reduce the leading edge stagnation temperature by 21% to 23%, and the maximum temperature difference on the surface of the structure is reduced by 64.8%. Reduce the thermal stress generated by the temperature gradient, effectively improve the thermal structure matching and material reliability in the high-temperature environment, and can be reused many times. Further engineering application research can be carried out for the specific structure and flight environment of the new generation aircraft.