摘要
介绍了一种新型发动机用外防热材料,该防热材料在短时间高热流的条件下,通过电弧风洞试验考核,试样的背壁温度可降低至144℃,相较于无涂层试样,背温的降温幅度高于300℃。0.5 mm厚涂层与0.8mm厚涂层相比,试样背温并无明显优势。且室温固化涂层比高温固化涂层试样背壁温度低30℃,均低于234℃,均满足设计指标要求的背壁温度低于350℃的使用需求。
This paper presents an innovative thermal protection coating material for solid rocket motors,that was subjected to high heat flux in a short time for arc-heated wind tunnel test.It is observed that the back surface of the coated samples with thermal protection coating can be cooled to 144℃ with a drop of 300℃ at least in comparison with that of the uncoated samples.The results showed that the back temperature of the samples with 0.5 mm coating was little superior to that in the case of 0.8 mm coating.Moreover,the back temperature of the coated samples cured at room temperature with a drop of 30℃ by contrast with that of the samples cured at high temperature,and the samples in both cases have the back temperature below 234℃ in accordance with the design value of less than 350℃.
出处
《宇航材料工艺》
CAS
CSCD
北大核心
2014年第3期69-72,共4页
Aerospace Materials & Technology
关键词
防热材料
烧蚀
风洞
Thermal protection material
Ablation
Wind tunnel
