固液火箭发动机推进剂组合能量特性分析

Analysis of the energy characteristics of hybrid rocket motor propellant combinations

对固液火箭发动机常用燃料和氧化剂进行了总结,计算了常用推进剂组合的能量特性。在常用的推进剂组合中,燃料HTPB(端羟基聚丁二烯)、Paraffin(石蜡)和PE(聚乙烯)分别与同种氧化剂组合后的能量性能较接近,氧化剂LOX(液氧)与燃料组合后的真空比冲较高,98%H2O2与燃料组合后的密度比冲较高。对HTPB基燃料中加入添加物对发动机性能影响的单因素分析和正交试验设计表明,Al、AlH3、AP、B 4种添加物均使发动机最佳氧燃比值减小,AlH3对真空比冲的提高作用最显著,Al对密度比冲的提高作用最显著,各种添加物间的交互影响作用不明显。

The most common fuels and oxidizers of hybrid rocket motor were summarized, and the energy characteristics of different propellant combinations were presented. In the normal propellant combinations, the energy characteristics of the fuel HTPB, Paraffin and PE（polyethylene） combining with the same oxidizer are proximal. For the oxidizer, LOX can provide higher vacuum specific impulse, while the density specific impulse of 98% H202 is higher. According to the single factor analysis and orthogonal experimental design, the influences of the additives on the fuel HTPB were analyzed. The results indicate that the additives A1, A1H3 , AP（ ammonium perchlorate） and B decrease the optimum oxidizer-to-fuel ratio. The enhancement effect of the additive A1H3 on the vacuum specific impulse is the most significant, and A1 is the most effective additive to improve the density specific impulse. The interaction of different additives is not obvious.