摘要
直径及开口都较大的固体火箭发动机燃烧室大都采用橡胶基绝热层,但是,对于长细比大,或者是开口较小的客体,采用橡胶基绝热层在工艺上难以实现。为了寻找同时具备隔热效果良好,且针对小口径壳体工艺可行性高的内防热材料,我们开展了以环氧树脂、橡胶为基体,云母粉等耐高温无机填料组成的防热材料。通过试件测试及产品验证,证明该防热涂层也是固发燃烧室一种较为适宜的烧蚀防热材料,它不受被保护产品的几何形状限制,烧蚀率较小。
The diameter and the openings are larger solid rocket engine combustion chamber mostly use rubber insula- tion layer, however, the slenderness ratio, or is the object of opening a smaller, the rubber insulation in the process to achieve. In order to find and has good heat insulation effect, and the small caliber shell process feasibility of high internal thermal protection material, we carried out with epoxy resin, rubber as matrix, mica and other high temperature inorganic filler heat protection material. Through the specimen test and product verification, proved that the thermal insulation coating. The combustion chamber is also a suitable ablative materials, it is not affected by the geometry constraints protection products, the ablation rate.
出处
《装备制造技术》
2013年第11期274-275,共2页
Equipment Manufacturing Technology
关键词
固体火箭发动机
隔热
内防热
solid propellant rocket engine
thermal insulation
internal heat
