固液火箭发动机内弹道参数的计算  

Calculation Study on Interior Ballistics Parameters of Hybrid Rocket Motor

作　　者：张梦龙 张悦 刘洋[1] ZHANG Menglong;ZHANG Yue;LIU Yang(The No.91550 th Troop of PLA,Dalian 116023,China)

机构地区：[1]中国人民解放军91550部队

出　　处：《兵器装备工程学报》2018年第10期28-32,共5页Journal of Ordnance Equipment Engineering

摘　　要：针对固液火箭发动机中的内弹道计算,建立了采用最小吉布斯自由能法进行热力计算的模型,并根据化学平衡理论,计算了发动机工作过程中的内弹道参数。应用该方法计算了某固液试验发动机燃烧室的内弹道,得到了燃面退移速率、室压、比冲和推力等参数值,并与固液发动机的数值模拟结果进行了对比分析。通过对比发现,两者计算的内弹道参数基本一致,而且均符合固液发动机的燃烧规律,说明该方法对固液火箭发动机的内弹道计算具有较强的实用性。For the calculation of internal trajectory in solid-liquid rocket engines,a thermodynamic calculation model using the minimum gibbs free energy method is established.Based on the equilibrium assumption,the interior ballistics parameters were calculated by this model.With this method,the interior ballistics parameters of the hybrid rocket motor were calculated,such as the regression rate,the chamber pressure,the specific impulse,the thrust and so on,and were compared with the numerical simulation results.The compared results show that the two methods were basically identical,and all results agreed well with the combustion law in hybrid rocket motor.The calculation model can be widely used in the interior ballistics parameters of the hybrid rocket motor.

关 键 词：固液火箭发动机 内弹道 退移速率 数值模拟 

分 类 号：TJ763[兵器科学与技术—武器系统与运用工程]