镁铝富燃料推进剂燃烧性能研究  

Study on combustion performance of magnesium-aluminum fuel-rich propellants

作　　者：聂芝侠[1] 李葆萱[1] 胡松启[1] 王英红[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243-246,共4页Journal of Solid Rocket Technology

摘　　要：为了研究镁铝富燃料推进剂燃烧性能，采用捏合机混合物料、真空浇注、恒温固化的方法制备推进剂试样，用靶线法测试推进荆燃速（0．5～2.0MPa），用Vieille经验公式r=ap^n计算压强指数。研究表明，细粒度AP含量增加，燃速逐渐增加，而压强指数先升高后降低。采用复合催化剂GFP／Fe：O，可同时提高燃速和压强指数。当催化剂质量含量为5％时，改变GFP／Fe2O3比对推进剂的燃速及压强指数的影响与氧化剂AP级配有关。对于细粒度AP含量高的配方，GFP／Fe2O3对燃速和压强指数影响较大。金属含量对燃速影响较大，对压强指数影响很小。而Mg／Al比对燃速和压强指数影响都很小。随着氧化剂中KP含量增大，燃速呈下降趋势，压强指数先升高后下降。In order to investigate combustion performance of magnesium-aluminum fuel-rich solid propellants, the propellant samples were prepared by mixing ingredients in kneading machine, vacuum casting and constant temperature curing methods. The burning rate of propellant （ at 0.5 -2.0 MPa） was measured by strand burner method, and the pressure exponent was calculated by Vieille empirical formula r=ap^n, The results show that with increase of fine AP content,the burning rate increases gradually;but pressure exponent first rises,then drops down. The burning rate and pressure exponent can be improved by adding catalyst GFP/ Fe2O3. When the content of catalyst is up to 5%, the effects of GFP/Fe20s content ratio on the burning rate and pressure exponent have relations with AP graduation. For the propellant with high-content fine AP, GFP/Fe2O3 content ratio has great effect on the burning rate and pressure exponent. The metal content also has great effect on the burning rate, but a little effect on pressure exponent. While Mg/Al content ratio has small effect on burning rate and pressure exponent. With the increase of KP content, the burning rate decreases, and the pressure exponent first rises, then drops down.

关 键 词：富燃料推进剂 燃速 压强指数 

分 类 号：V512[航空宇航科学与技术—航空宇航推进理论与工程]