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

作　　者：夏吝时 杨凯威 那伟[1] 陈政伟[1] 马贵春[2] XIA Linshi;YANG Kaiwei;NA Wei;CHEN Zhengwei;MA Guichun(Thermal Protection Test Center,Beijing Institute of Space Long March Vehicle,Beijing 100076,China;Institute of Mechanical Engineering,North University of China,Taiyuan 030051,China)

机构地区：[1]北京航天长征飞行器研究所防隔热试验中心,北京100076 [2]中北大学机电工程学院,山西太原030051

出　　处：《热科学与技术》2023年第5期498-505,共8页Journal of Thermal Science and Technology

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。To avoid the aerodynamic ablation of the aircraft rudder and wing during the long range flight in near space,the alkali metal was used as the working fluid,and a Ni-based alloy device with high-temperature thermal conduction capability was installed between the high thermal conductivity C/C heat shield and carbon-based flexible high thermal conductivity layer.The tests under different flight environment conditions were carried out by using the profiling quartz lamp heater.The overall heat transfer capacity and thermal protection effect were analyzed by numerical analysis.The results show that the effective thermal conductivity increases from 18.42 to 1390.00 W/(m·K)when the Ni-based alloy device is activated,the leading edge stagnation temperature decreases by 21.70%to 23.04%,and the maximum temperature difference on the surface of the structure decreases by 64.80%,This method reduces the thermal stress generated by the temperature gradient and effectively improves the thermal structure matching performance and material reliability in a high-temperature environment.Further engineering application research can be carried out for the specific structure and flight environment of a new generation of aircraft.

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 

分 类 号：V416.5[航空宇航科学与技术—航空宇航推进理论与工程] TK124[动力工程及工程热物理—工程热物理]