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本文研究了固冲发动机含铝推进剂的燃烧过程,为了合理组织主、次流的掺混流场,选用不同型式的火箭喷管进行试验。测量了四孔非平行进气的次流静压分布;单独主流的总、静压分布;音速单喷管等六种喷管的主次流掺混流场的速度场。 本文分析了铝颗粒完全燃烧的三条件,并结合火箭喷管型式对冲压室内掺混流场的分析,选用了具有4×φ12—15°斜喷口的多孔分流式亚音速喷管为火箭喷管,进行了燃烧效率试验。实验结果表明,冲压室燃烧效率比采用音速(或超音速)单喷管时提高30％左右。 燃烧效率试验用的装药为含铝贫氧推进剂,重量5.5—8.9公斤,工作时间14—23秒。
In this paper, the combustion process of solid propellant aluminum-containing propellants is studied. In order to organize the mixing flow field of primary and secondary flow reasonably, different types of rocket lances are selected for testing. The four-hole non-parallel intake air was measured for the distribution of the secondary hydrostatic pressure; the total main and the static pressure distribution of the single mainstream; In this paper, the three conditions of complete combustion of aluminum particles are analyzed. Combined with the rocket nozzle type analysis of the mixing flow field in the stamping chamber, the porous split-flow subsonic nozzle with 4 × φ12-15 ° inclined nozzle is selected as the rocket nozzle , Conducted a combustion efficiency test. The experimental results show that the combustion chamber ramification efficiency than the use of sonic (or supersonic) single nozzle increased by about 30%. Burning efficiency test for the loading of aluminum-containing oxygen-poor propellant, weight 5.5-8.9 kg, working time 14-23 seconds.