采用液体喷射实现固体发动机主动冷却的探索研究  

Exploratory research on active cooling of SRM by means of liquid injection

作　　者：陆晋丽[1] 何国强[1] 李江[1] 刘佩进[1] 秦飞[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《固体火箭技术》2008年第3期239-242,共4页Journal of Solid Rocket Technology

摘　　要：为寻找固体发动机热防护的新途径,开展了固体发动机液体喷射主动冷却的探索性研究。组建了1套固体发动机液体喷射主动冷却试验系统,开展了原理试验。水作为冷却工质,沿收敛段壁面喷射,试验中对内壁面和外壁面处的温度进行了测量。试验结果表明,冷却工质的引入大大降低了发动机收敛段内壁面的温度,但会造成一定比冲损失;冷却工质参与做功,发动机推力有所增加。建立了液体冷却固体发动机的性能计算模型,并用试验结果进行了校验;根据试验得到了冷却效能估计经验公式。Exploratory research on active cooling of SRM by means of liquid injection was carried out to find out the new ways for thermal protection of SRM. A set of active cooling test system with liquid injection was built. The principle test was carried out. Water was chosen as coolant ,which injected along the inner surface of convergence section. The temperatures of inner surface and external surface were measured. The experiment results show that introduction of coolant lowers the temperature of inner surface greatly, but may cause certain specific impulse loss. Because the coolant takes part in doing work, the thrust increases. Calculation model for property of SRM with liquid injection was derived and validated by the experiment results. The empirical formula on cooling efficiency was obtained by means of the experiment,

关 键 词：固体推进剂火箭发动机 热防护 主动冷却试验 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]