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设计了一种新的收集固体火箭发动机喷管凝相颗粒的实验装置,针对典型的HTPB复合推进剂,开展了喷管喉部凝相颗粒的收集实验和粒度分析,研究了燃烧室压强和收敛角度对喷管喉部颗粒粒度分布的影响规律。研究结果表明,喷管喉部的凝相颗粒在0.27～50μm之间都有颗粒存在,凝相颗粒主要集中在0.3～15μm之间,粒径大于15μm的颗粒较少;燃烧室压强对颗粒粒径有较大影响,随着燃烧室压强的升高,凝相颗粒粒径变小,粒度分布更为集中;燃烧室压强相同的条件下,收敛角度对喷管喉部的凝相颗粒粒度分布影响较小。
A new experimental apparatus for collecting condensed phase particles of solid rocket motor nozzle was designed. For the typical HTPB composite propellant, the experiment of collecting throat coagulation particles and particle size analysis were carried out. The effects of pressure and convergence in the combustion chamber Influence of Angle on Particle Size Distribution of Nozzle Throat. The results show that there are particles between 0.27 ~ 50μm in the throat of the nozzle, the coagulation particles are mainly concentrated in the range of 0.3 ~ 15μm, and the particles with the particle size larger than 15μm are less; The diameter of condensed phase particles becomes smaller and the particle size distribution is more concentrated. With the same pressure in the combustion chamber, the angle of convergence of condensed phase particle size distribution Less affected.