摘要
介绍某固体发动机壳体外防热涂层的研究情况。通过各种基体材料的选择研究 ,确定所研制涂料由有机硅改性环氧树脂室温固化体系与耐热和隔热功能填料组成 ;溶剂为丙酮和二甲苯的混合物。涂层的拉伸强度≮ 7MPa ;伸长率≮ 1 % ;热导率为 0 .2 2 1W/ (m·K) ,比热容为 1 .72× 1 0 3J/ (kg·K) ,密度为 1 .2 5 6g/cm3;并具有较高的耐热性。
This paper deals with the study of the external thermal insulation coating for a solid rocket motor (SRM) case. By comparing several materials, an epoxy silicone resin cured at room temperature is selected as the matrix of the coating.The solvent is a mixture of acetone and xylene.Tensile strength of the coating is above 7 MPa and tensile elongation is above 1%.Thermal conductivity,specific heat capacity and density of the coating is 0.221 W/(m·K), 1.72×10 3 J/(kg·K) and 1.256 g/cm 3 respectively.At the same time, the coating′s capability of heat resistance, thermal insulation and adhesion are also very good.
出处
《宇航材料工艺》
CAS
CSCD
北大核心
2003年第3期21-24,共4页
Aerospace Materials & Technology
