N_2O-PMMA小型混合火箭发动机试验研究

Experimental investigation of N_2O-PMMA lab-scale hybrid rocket motor

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。

A test bench for a lab-scale N2O-PMMA hybrid rocket motor was developed to test a motor prototype. The testing bench and the hybrid rocket motor were evaluated in a series of firings. Performance data for a running motor was used to model the PMMA regression rate and the oxidizer mass flux through curve fits of the test data. The influence of fuel grain length and port diameter, oxidizer mass flux and nozzle throat diameter on the combustion efficiency and propulsion performance was then analyzed in further tests to optimize these parameters. The testing system and experimental method provide the basis for optimization and future studies of lab-scale hybrid rocket motors.