高超声速飞行器前缘疏导式热防护结构的实验研究  

Experimental investigation of dredging thermal protection system of hypersonic vehicle leading edge

作　　者：孙健[1,2] 刘伟强[2] 

机构地区：[1]中国人民解放军92941部队93分队 [2]国防科技大学高超声速冲压发动机技术重点实验室

出　　处：《物理学报》2014年第9期201-208,共8页Acta Physica Sinica

基　　金：国家自然科学基金(批准号:90916018);高等学校博士学科点专项科研基金(批准号:200899980006)资助的课题~~

摘　　要：针对高超声速飞行器前缘疏导式防热结构的特点,设计前缘内嵌高导热率材料结构和一体化层板热管结构两类对比实验,用于验证前缘疏导式防热结构的可行性.利用球形短弧氙灯作为辐射热源模拟气动加热,分别对钢质前缘、内嵌铜材料的钢质前缘和一体化层板式热管前缘进行加热,测量前缘驻点区域和尾部翼面区域的温度变化.实验结果表明:内嵌高导热率材料的前缘疏导结构能够降低头部驻点区的温度,提高尾部低温区的温度,实现对前缘结构的热防护;以蒸馏水作为工质一体化层板式热管前缘结构,在较低热流条件下也能够实现对前缘驻点区的疏导式热防护,但在较高热流条件下,由于水蒸气压力过大使得层板式前缘结构发生破坏,体现出热管内部工作介质对结构防热效果和应用范围都起到的关键作用.According to the characteristics of dredging thermal protection system （DTPS） of hypersonic vehicle leading edge, both the structure of embedded high conductivity materials and that of integrative plate of heat pipe are designed to complete the two kinds of comparative experiments so as to prove the feasibility of the DTPS. As a source of radiation heating, the spherical short arc xenon lamp is simulated for aerodynamic heating. The pure steel leading edge, the embedded copper leading edge, the plate pure steel leading edge, and the integrative plate for heat pipe leading edge are heated respectively. Temperature variations of stagnation point region and tail fins are measured. Experimental results show that DTPS of the embedded high conductivity materials can reduce the temperature of stagnation point region and increase the temperature of the tail fins. It also can achieve the aim of thermal protection of leading edge. The DTPS of integrative plate heat pipe whose working fluid is pure water also can protect the leading edge under the condition of low heat flux. At the huge pressure of vapor, DTPS of the integrative plate of heat pipe may be broken at high heat flux. It is shown that the working fluid of heat pipe can play a key role in the application range for the thermal protection effect.

关 键 词：前缘 疏导式热防护 热管 层板 

分 类 号：O426.9[理学—声学]