固体发动机有机烧蚀防热涂层的研究

STUDY OF ORGANIC ABLATIVE THERMAL-PROTECTION COATING FOR SOLID ROCKET MOTOR

关键词:  固体火箭发动机  隔热  有机涂层  防护涂层  研究

Key words:  Solid rocket  Thermal insulation  Organic coating  protective coating  Research

摘要:

直径、开口较大的固体发动机燃烧室热防护大多采用橡胶基绝热层、但对长细比较大,特别是开口甚小的金屈壳体工艺上却难以实施。 为了寻找具有良好的防热效果,同时工艺又简便易行的发动机内防热材料。我们开展了以环氧树脂为粘合剂、Al₂O₃·3H₂O为阻燃剂,添加石英粉、Cr₂O₃等耐高温、低导热性能无机填料组成的防热涂层的试验研究。 通过试片试验与发动机地面考核试验,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,它具有不受被保护产品几何形状的限制。可采取喷涂、滚涂、刮涂、刷涂等优点,烧蚀率远小于橡胶基绝热层,尤其适用工作时间在30s左右的战术型号发动机燃烧室热防护。

Abstract:

Rubber-base insulation is generally used as thermal-prorection meterial for combustion chamber of solid rocket motor whose diameter and forword and aft opening of case is large. Howere, when it is used as thermal-protection materia for combustion chamber of solid rocket motor whose slenderness ratior and foward and aft opening of case is small, process is more difficult.In order to find out a new interior thermal-protection material which prossesses good thermal-protection performance and simple manufacturing technique, epoxy resin used as binder, Al2O3 used as burning inhibitor, quartz powder and Cr2O3 are experimentally investigated.The experiment and test show the tollowing results: the new thermall-protection coating is suitable of ablative insulation material of solid rocket motor. Manufacturing technique is not restricted to only some geometric shap of solid rocket motor. Its ablation ratio is even smaller than that of rubber-base insulation. And it is especially suitable for tactical motor.