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首页> 外文期刊>Journal of propulsion and power >Fuel Regression Characteristics of a Novel Axial-Injection End-Burning Hybrid Rocket
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Fuel Regression Characteristics of a Novel Axial-Injection End-Burning Hybrid Rocket

机译：新型轴喷端燃混合火箭的燃料回归特性

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摘要

The regression characteristics of axial-injection end-burning hybrid rocket were experimentally investigated using a laboratory-scale motor. The axial-injection end-burning type fuel grains were made by high-accuracy three-dimensional printing. Firing tests were conducted using gaseous oxygen as the oxidizer at a chamber pressure range of 0.10 to 0.43 MPa. Results of 15 static firings tests show that fuel regression rate increases as the chamber pressure rises, and fuel regression rate decreases as the oxidizer port velocity increases. A data reduction method was developed to avoid the difficulty in calculating oxidizer-to-fuel ratio. A simplified fuel regression model based on the granular diffusion flame model is developed to investigate regression characteristics. The trend in results as calculated using the granular diffusion flame model agrees with that in experimentally observe values. However, this does not hold true in tests with varying oxidizer port velocity. A granular diffusion flame model only takes into account simple solid propellant regression. Therefore, modification of the model is needed for calculating the fuel regression rate of an end-burning hybrid rocket
机译：使用实验室规模的发动机，对轴向注入式端燃烧混合火箭的回归特性进行了实验研究。轴向喷射端燃型燃料颗粒是通过高精度的三维印刷制成的。使用气态氧作为氧化剂在0.10至0.43 MPa的腔室压力范围内进行点火测试。 15次静态点火测试的结果表明，随着腔室压力的升高，燃料的退化率增加；随着氧化剂端口速度的增加，燃料的退化率降低。为了避免计算氧化剂/燃料比的困难，开发了一种数据简化方法。建立了基于颗粒扩散火焰模型的简化燃料回归模型，以研究回归特性。使用颗粒扩散火焰模型计算得出的结果趋势与实验观察值一致。但是，这在氧化剂端口速度变化的测试中并不成立。颗粒扩散火焰模型仅考虑简单的固体推进剂回归。因此，需要对模型进行修改以计算端燃烧混合动力火箭的燃料回归率

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