非烧蚀型防热材料烧蚀性能初步试验研究(英文)  

Preliminary tests of non-ablative thermal protection materials

作　　者：刘初平[1] 孟松鹤[1] 杜百合[2] 王国林[2] 

机构地区：[1]哈尔滨工业大学航天学院,哈尔滨150001 [2]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《实验流体力学》2009年第3期50-53,69,共5页Journal of Experiments in Fluid Mechanics

摘　　要：介绍了在CARDC等离子体风洞中开展的非烧蚀型防热材料超高温陶瓷(UHTC)的试验研究结果。对Ф20mm平头圆柱体试验模型,采用亚声速驻点试验技术,在驻点热流478 W/cm2,气流焓值27.9MJ/kg,环境压力18kPa条件下,分别对代号C(15、10)型、Y型、S(30、15、10)型3种材料模型进行了试验研究,并对模型试验前后的长度变化、质量变化以及模型表面温度进行了测量,初步分析了模型的表观变化、抗氧化特性和表面辐射特性。结果表明:Y型模型试验前后表观变化不大,表面温度达到1930℃;S型模型表面生成一层薄氧化层,稳定情形下模型表面温度达到1964℃;C型模型表面烧蚀严重,模型表面温度达到2462℃,防热性能最差。The test results of non-ablative ultra-high temperature ceramic materials （UHTC） in one of the plasma wind tunnels of CARDC are introduced in this paper. Three types of materials,namely model C（15, 10）,Y and S（30,15,10）, were tested under a subsonic condition with stagnation point heat flux of 478W/ cm^2, enthalpy of 27.9 MJ/kg and stagnation point pressure of 18kPa. The test models were in flat cylinder shape with a diameter of 20mm. The length variation and mass loss and surface temperature of each test model were measured . Test results showed that model Y surface temperature reached 1930℃ with little surface characteristics change,model S surface temperature reached 1964℃ with an oxidation layer formed and model C surface temperature reached 2462 ℃ yet experienced severe ablation. Preliminary analyses of the tested materials in terms of surface characteristics change, anti-oxidation characteristics and surface radiation characteristics are also presented.

关 键 词：超高温陶瓷 等离子体风洞 烧蚀试验 

分 类 号：V211.73[航空宇航科学与技术—航空宇航推进理论与工程]