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为研究小型氧化二氮(N2O)-有机玻璃(PMMA)混合火箭发动机,搭建了试验平台,设计并制造了N2O-PM-MA混合发动机试验样机。通过试验验证了试验平台和发动机设计,获得了N2O-PMMA混合发动机燃料燃速和氧化剂质量速度的关系公式。利用试验数据分析了燃料药柱几何尺寸、氧化剂质量速度和发动机喷嘴喉径对燃烧效率及推进性能的影响,探讨了这种发动机的优化设计范围。研究结果为未来小型混合发动机的工程应用提供了试验平台和科学依据。
In order to study the small N2O-PMMA hybrid rocket engine, a test platform was set up and the N2O-PM-MA hybrid engine prototype was designed and manufactured. The experimental platform and engine design were validated through experiments, and the formula of the relationship between the fuel burning speed and the mass velocity of oxidant was obtained. The experimental data were used to analyze the influence of the geometry of fuel pellets, the mass velocity of oxidant and the throat diameter of engine nozzle on the combustion efficiency and propulsion performance. The optimal design range of this engine was discussed. The research results provide the experimental platform and scientific basis for the engineering application of small hybrid engine in the future.