摘要
介绍了某联合动力装置中的共底和环形点火器首次采用新研制的３５００Ｋ高温涂料进行热防护的配方设计、受热计算、涂层制备和试验考核。由环氧改性有机硅树脂基料、专用树脂固化体系和多种形状的硅酸盐填料制成的涂层具有优异的耐高温、隔热和抗烧蚀性能，还能紧温固化成形，成功地解决了中型固体火箭发动机中大尺寸、薄壁、复杂型面零件的热防护和过烧蚀难题，有效地提高了发动机的工作可靠性。
research in formulation design,heating calculation,coating preparation and examining test for thermal protection of the common dome and ring ignitor is presented. An advanced 3500K high temperature coating is first used in a powerplant,which is made of epoxy organosilicon resin substrate, special resin curing system and multi-shape silicate filler. The performances of the coating in high temperature resisting, thermal insulating and ablation resisting are excellant. Also, the coating can be cured and shaped at a room temperature. It solves successfully the difficult problems of thermal protection and overablation for the parts which have large dimension, thin wall and complex geometric shape in the medium solid rocket motor,and increases effectively the operating reliability of motors.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1995年第5期65-71,共7页
Journal of Propulsion Technology
关键词
固体推进剂
火箭发动机
耐热涂层
热防护
烧蚀
Solid propellant rocket engine, Heat resistant coating, Thermal protection, Ablation
