固液火箭发动机试验瞬时燃速分析方法

介绍了一种用于固液火箭发动机试验的瞬时燃速分析方法,运用该方法对H2O2/HTPB固液火箭发动机单室双推力长时间热试车试验进行燃速分析,拟合得到该工况下的燃速公式为r=1.847×10-2G0o.7304。根据燃速公式等计算结果对一次发动机试验进行了预估,计算得到的预估内弹道性能曲线与试验结果吻合较好,验证了该瞬时燃速分析方法的可行性,为发动机工作时间较长、氧化剂流率变化较大时的燃速分析提供了一种途径。

Instantaneous Fuel Regression Rate Analysis of Hybrid Rocket Motor Experiment

This paper proposes an instantaneous fuel regression rate analysis method for hybrid rocket motor experiment when the oxidizer mass flux changes large during a long working time.The method is applied on a single-chamber dual-thrust hybrid rocket long-time test with the hydrogen peroxide(H2O2) and hydroxyl-terminated polybutadiene(HTPB) propellant combination,and the fuel regression rate formula,=1.847×10-2G0.7304o,is fitted based on the analysis results.According to the fitted fuel regression rate formula and calculation results,the prediction performances of a test are produced.The results show that the prediction interior ballistics performances fit well with the test curves,which validates the feasibility of the analysis method.