铝镁贫氧推进剂的点火性能  

Ignition Performance of Fuel-rich Solid Propellants Containing Magnesium-Aluminum

作　　者：肖秀友[1] 李葆萱[1] 王玉玲[2] 王英红[1] 胡松起[1] 

机构地区：[1]西北工业大学航天学院,陕西西安710072 [2]第二炮兵工程学院,陕西西安710025

出　　处：《火炸药学报》2005年第1期15-18,共4页Chinese Journal of Explosives & Propellants

摘　　要：为研究镁铝富燃料固体推进剂组分对点火性能的影响,采用改进的靶线法燃速测试系统对多种含镁铝富燃料固体推进剂在常压和加压下进行了通电金属丝点火性能的对比实验。被测试推进剂的镁铝合金含量为20%～40%,或者同时含镁铝合金及硼,氧化剂含量为30%～53%。实验表明,在固定外界输入热源的情况下,推进剂的点火性能主要与氧化剂含量和粒度有关;金属的含量和种类也有一定的影响;催化剂对点火延迟时间影响很小;压强对此种点火方式几乎无影响。该点火延迟测试方法简单易行,并具有一定的可靠度,适于配方调试。The ignition performance of fuel-rich propellants which contain metal fuel such as Magnesium-Aluminum powders or combines of Magnesium-Aluminum powders and Boron powders is measured with Crawford bomb and the pressure conditions of ignition experiment are atmosphere and pressurized separately. The contents of AP oxidizer and Magnesium-Aluminum alloy fuel in propellant samples are from 30% to 53% and from 20% to 40% respectively. Experimental results reveal that the ignition performances of propellant samples under the fixed heat input condition are closely related to oxidizer content and its particle size distribution. The kinds of metal fuel as well as its contents also have influences on ignition delay time in some degree. The catalyst and pressure almost have no effects on ignition delay time. The method of testing ignition delay is simple, easy and reliable, and can satisfy the need of tailoring fuel-rich propellant formulations.

关 键 词：贫氧富燃料推进剂 点火性能 燃烧性能 

分 类 号：V51[航空宇航科学与技术—航空宇航推进理论与工程]