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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。
An instantaneous burning rate analysis method for solid-liquid rocket engine test is introduced. By using this method, the burning rate of H2O2 / HTPB solid-liquid rocket engine single-chamber double-thrust long time heat test is analyzed. The burning rate formula is r = 1.847 × 10-2G0o.7304. According to the calculation results of combustion rate formula and so on, an engine test is estimated. The predicted internal ballistic performance curve is in good agreement with the experimental result, which verifies the feasibility of the instantaneous combustion rate analysis method. , The oxidizer flow rate changes when the burning rate provides a way to analyze.