液体推进剂液滴电点火特性的实验研究  

Experimental Study on Electrical Ignition Properties of Liquid Propellant Droplet

作　　者：余永刚[1] 李明[1] 周彦煌[1] 陆欣[1] 

机构地区：[1]南京理工大学动力工程学院,江苏南京210094

出　　处：《含能材料》2008年第5期625-628,共4页Chinese Journal of Energetic Materials

基　　金：国家自然科学基金(50776048)

摘　　要：为了研究HAN基液体推进剂电点火特性,设计了液体推进剂液滴低压电加热点火模拟试验装置,利用高速录像系统,观测了HAN基液体推进剂LP1846单滴在不同电加热速率下的点火特性,结果表明,LP1846液滴在通电时主要经历四个特征过程,即:蒸发过程、周期性膨胀收缩过程、热分解过程和着火燃烧过程,且在膨胀收缩过程中伴有微爆现象发生。电压加载速率从80 V.s-1增大到140 V.s-1过程中,液滴着火延迟期从0.82 s变为0.62 s,呈线性缩短,且着火时火焰越明亮。In order to study the electrical ignition properties of HAN-based liquid propellant, an experimental device of electrical heating ignition of liquid propellant droplet was designed. By using high speed camera system, the ignition properties of LP1846 single droplet was observed at different electrical heating rates. The results show that when the LP1846 droplet is electrified,it goes mainly through four characteristic processes,i, e. evaporization process,periodic expansion and contraction process,stronger thermal decomposition process,and ignition and combustion process. When peak load voltage is from 80 V·s^-1 to 140 V·s^-1 ,the ignition delay time of LP1846 droplet is linearly shorten from 0. 82 s to 0.62 s,but the flame is lighter.

关 键 词：燃烧学 液体推进剂 电点火 瞬态测量 

分 类 号：V511[航空宇航科学与技术—航空宇航推进理论与工程]