Abstract: Investigated charring erosive characters of internal insulation of solid rocket motor under flight acceleration. Performed the ablation tests of NBR and EPDM insulation on rotating test system using erosive motor. When acceleration is 70g, pressure is 5 MPa, time is 10s,the flight enhancement factor of insulation is less than 1 7. The experiment result can use to internal insulation design of solid rocket motor.

Key words: Solid propellant rocket engine;Dome;Heat insulation layor;Ablation test;Acceleration

摘要： 研究了固体火箭发动机内绝热层在飞行加速度条件下的炭化烧蚀特性。用烧蚀发动机在旋转实验装置上 ,对 NBR和 EPDM绝热层试件进行了烧蚀实验。在加速度 70 g、压强 5MPa、时间 1 0 s条件下 ,绝热层平均炭化烧蚀率增大系数小于 1 .7。实验结果可作为发动机绝热层设计的依据

关键词: 固体推进剂火箭发动机;封头;绝热层;烧蚀试验;加速度