Abstract: 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 -2G0.7304_o, 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. 

Key words: Hybrid rocket motor; Instantaneous fuel regression rate; Ground experiment, Interior ballistics

摘要： 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=1.847×10-2G0.7304o 。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。 

关键词: 固液火箭发动机;瞬时燃速;地面试验;内弹道