宽压强范围少烟无铝推进剂燃烧性能研究

针对固体火箭发动机对少烟无铝推进剂的需求，研究了宽压强范围（1~22MPa）少烟无铝推进剂的燃烧性能。通过添加高熔点燃烧稳定剂、压指调节剂复配等技术手段，采用静态燃速测试仪、标准试验发动机、全尺寸发动机以及静态烟箱法等研究了推进剂燃速、压强指数、能量性能和烟雾特征信号与燃烧稳定剂（CW-1）、复合压指调节剂（YZJ-A/B）含量的变化规律。试验结果表明：（1）采用高熔点的燃烧稳定剂（CW-1）取代铝粉，当燃烧稳定剂用量在1%~4%，推进剂在1~22MPa宽压强范围内可以稳定燃烧。（2）燃烧稳定剂（CW-1）取代铝粉后，推进剂比冲下降，烟雾特征信号降低。（3）添加有机钡盐和季铵盐-二茂铁类复合压指调节剂（YZJ-A/B），推进剂在17 ~22MPa动态压强指数由0.39降低至0.275。

Combustion Performance of Reduced Smoke and Aluminum-Free Propellant in Wide Pressure Range

In order to meet the demand of solid rocket motor on the reduced smoke and Aluminum-free propellant, combustion performance of this type of propellant within wide pressure range from 1MPa to 22MPa was investigated. By adding high-melting-point burning stabilizer and adopting compound pressure exponent modifier, the effects of burning stabilizer(CW-1) and composite pressure exponent modifier(YZJ-A/B) on burning rate, pressure exponent, energy performances and smoke characteristic signal were studied , using static burning rate tester, standard test motor, full-size rocket motor and static smoke box tester. Results show that the propellant can burn stably at pressure of 1 to 22MPa, when a part of Aluminum powder that takes 1% to 4% of whole propellant was replaced by high-melting-point burning stabilizer (CW-1). In this condition, the propellant specific impulse and smoke characteristic signal decrease. When composite pressure exponent modifier including organic barium salt and quaternary ammonium salt- ferrocene salt (YZJ-A/B) are added, the propellant dynamic pressure exponent at 17 to 22MPa decreases from 0.39 to 0.275.