固体火箭发动机内绝热层烧蚀率实验研究

根据固体火箭发动机内绝热层烧蚀环境,设计研制了一种绝热层烧蚀试验发动机。利用该发动机不仅可进行绝热材料配方筛选,而且通过调节压强、流速及冲刷角进行缩比发动机烧蚀模拟试验和各种烧蚀率影响因素分析。在大量实验研究的基础上,提出了一种能较精确测量绝热层烧蚀率的测试方法和实验评定方法。分析了发动机工作压力、流速、气流冲刷角、裂纹,脱粘、气孔、夹层及搭接缝对绝热层烧蚀率的影响。测试结果与实际发动机解剖数据有较好的一致性。

EXPERIMENTAL STUDY FOR ABLATION RATE OF SOLID ROCKET MOTOR INTERNAL INSULATION

A.test motor for screening and evaluating candidate insulation materials was designed and a technique for determining the average ablation rate of internal insulation materials was developed on the basis of many experiments in this paper. In subscale moter tests, material samples are placed inside this motor and internal pressure, velocity and angle of gases scouring are adjusted to approximate the full-scale motor conditions. Factors of insulation ablative rate, combustion gases pressure, gases velocity, angle of gases scouring, bonding seam and typical defects (craze, debonding, blowhole, inclusion), have been studied experimentally. The results are in agreement with measuring results of the full-scale motor.