模型脉冲爆震火箭发动机可爆范围的实验研究  

Experimental Investigation on Detonable Range of Pulse Detonations Rocket Engine Model

作　　者：范玮[1] 严传俊[1] 李强[1] 丁永强[1] 李江红[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《航空学报》2006年第5期737-741,共5页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(50106012;50336030);教育部优秀青年教师资助计划;新世纪优秀人才计划(NCET-04-0960)

摘　　要：在采用电磁阀控制间歇式供应的脉冲爆震火箭发动机模型上,研究了燃料、氧化剂的喷射占空比、喷射及点火的时序对两相爆震波形成的影响,得出了在一定供应条件下的可爆范围,掌握了控制规律。分析了这些影响的实质在于混合物的当量比和有效混合程度。实验结果表明,燃料/氧化剂喷射占空比应尽可能接近,并保证爆震管的有效填充,在此条件下应尽可能保证喷射相位一致,以达到最好的混合效果。The duty cycle for kerosene/oxygen injection and time sequence for injection, mixing and ignition to produce two phase and fully-developed detonations are investigated in a pulse detonation rocket engine model, which uses solenoid valves for intermittently supplying propellants. In some given supply conditions, the detonable ranges in terms of injection duty cycle and the control law are obtained. In the final analysis, these effects stem from the appropriate equivalence ratio and mixing. The experimental results show that to gain reli able detonations, the injection duty cycles for kerosene and oxygen should ensure enough filling first and then the injection time phases and duty cycles should keep as close as possible to attain the effective mixing.

关 键 词：两相爆震 可爆范围 实验研究 

分 类 号：V231.22[航空宇航科学与技术—航空宇航推进理论与工程]