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采用水下声发射法测试了推进剂静态燃速,用线性回归法计算了推进剂燃速压强指数;研究了GAP/CL-20高能固体推进剂中增塑比及固体组分AP、CL-20、Al粉粒度等配方组成因素对燃烧性能的影响。研究结果表明,增塑比一定范围内的变化不会对推进剂燃烧性能产生显著影响,其燃速和燃速压强指数基本不变;CL-20粒度减小或AP粒度增加均会导致燃速不同程度的降低,Al粒度减小也会使燃速减小,但在达到一定程度后,燃速又增加;推进剂燃速压强指数随CL-20、Al粉粒度减小和AP粒度增加而减小,并对其燃烧性能的影响机制进行了简单分析。
The static burning velocity of propellant was measured by underwater acoustic emission method and the burning rate pressure index of propellant was calculated by linear regression method. The effects of plasticizing ratio and solid components AP, CL- 20, Al powder particle size and other ingredients on the combustion performance of the impact. The results show that the change of plasticizing ratio within a certain range will not have a significant impact on the combustion performance of propellants, and its burning rate and burning rate pressure index are basically unchanged; the CL-20 particle size or AP particle size will increase the burning rate With different degrees of reduction, the decrease of Al particle size also decreases the burning rate, but after reaching a certain degree, the burning rate increases again. The burning rate pressure index of propellants decreases with the increase of CL-20, Al particle size and AP particle size Reduce, and its combustion performance of the mechanism of a simple analysis.