耐烧蚀防热隔热涂层的研制  

Development of Ablation and Heat-Resistant and Heat Insulation Coating

作　　者：张海鹏[1] 马天信[1] 张新航[1] 张崇耿[1] 

机构地区：[1]西安长峰机电研究所,西安710065

出　　处：《宇航材料工艺》2012年第5期69-71,共3页Aerospace Materials & Technology

摘　　要：根据某大型固体火箭发动机的飞行工作特性,在研究涂层的防热隔热机理的基础上,采用环氧改性有机硅树脂为基体树脂,加入耐温梯度分解混合填料及添加剂等制备了一种外防热涂层,并通过L9(33)正交实验确定了无机混合填料组分多聚磷酸铵、氢氧化铝和硼酸的最佳用量分别为4份、6份、3份。最后确定的涂层最佳配方试验结果:线烧蚀率为0.116 mm/s,热导率为0.28 W/(m.K),密度为1.28 g/cm3,附着力为11.84 MPa,表明该涂层具有良好的防热隔热性能且综合性能优良,满足了该固体火箭发动机的外部防热需求。According to identity of flying task in some solid rocket motor as well as the mechanism study of heat- resistant and heat insulation of coating, a kind of heat-resistant and heat insulation coating was prepared on the basis of epoxy resin grafted by silicone, mixed by temperature-resistant mixture filling and additive. The optimum parts of po- ly-phosphate ammonium,aluminium hydroxide and boric acid are 4,6,3 respectively, by using L9（33） orthogonal ex- periment. The results of the coating tests of the final optimum prescription：its line ablation rate is 0.116 mm/s, the heat conductivity is 0.28 W/（m · K）,the density is 1.28 g/cm3 ,the adhesion strength is 11.84 MPa,all show that the coating is of good combination of performances, especially good heat-resistant and heat insulation characteristics, which can satisfy the need of requirement of outer heat-resistant in solid rocket motor.

关 键 词：耐烧蚀 防热隔热 涂层 

分 类 号：V421[航空宇航科学与技术—飞行器设计]