摘要
针对实际使用的热环境要求,提出了多种防热结构材料及结构方案。通过石英灯加热试验对其防热性能进行了考核验证。考察了防热涂层、样件结构形式以及材料种类对试验件防热性能的影响。结果表明,防热涂层可显著降低防热试验件的背温,最高降幅达241℃;相对于传统的玻璃纤维/酚醛层压板结构,在满足防热要求的同时,新型蜂窝夹层结构的面密度较低,仅为层压板的50%左右,具有明显的减重优势,其中聚酰亚胺面板的蜂窝夹层结构的面密度仅为酚醛玻璃钢面板夹层结构的80%,其表面加防热涂层样件的背温仅为246℃。
Several thermal protection methods were proposed according to the thermal environment requirements in application. The thermal insulation property of different thermal protection materials and structures was tested by the quartz radiation heating method. The effects of thermal protection coating, structure and material on the thermal insulation property were investigated. Results show that the thermal protection coating can significantly lower the back temperature of the sample. Compared to the general glass fabric reinforced phenolic resin laminate panel, the sand- wich test panel prepared by glass fabric honeycomb and polyimide composite panel has lighter weight and good thermal insulation property. The area weight of honeycomb sandwich was only 50% of the laminate panel. And the area weight of sandwich with polyimide composite panel was about 80% of sandwich with phenolic composite panel. The back temperature of sandwich with polyimide panel covered by the thermal protection coating was only 246℃.
出处
《宇航材料工艺》
CAS
CSCD
北大核心
2012年第5期38-41,共4页
Aerospace Materials & Technology
关键词
防热材料
玻璃纤维/酚醛层压板
聚酰亚胺
蜂窝夹层结构
Thermal protection material, Glass fabric reinforced phenolic resin laminate panel, Polyimide, Honeycomb sandwich