摘要
为了探索液体火箭发动机的新型点火方法,设计了一种周期性序列脉冲放电火化的模拟点火装置,该装置采用电机驱动电极转动,在圆周上形成放电火化的时空分布。采用高速录像系统,开展了HAN基液体推进剂LP1846液雾在不同条件下电点火特性的实验研究,结果表明,电极转速在3～5 r/s时,电火化在圆周放电空间内的分布比较密集,电能时空分布比较均匀,LP1846液雾点火效果较好。喷雾场流速、液雾细度与周向放电火化能量分布存在一个最佳匹配关系。
An ignition device of periodicity sequence pulse discharge has been designed to explore a new way for the liquid rocket ignition. In the device, turning of the electrode is derived by electric motor and the sparks distribute in sequence on circumference space. By using of high speed camera system, the study is conducted about the electric ignition mechanism of HAN-Based liquid propellant LP1846 under different condition. The results show that, the sparks are dense in the circumference discharge space when the revolving speed of the electric motor is 3-5 r/s, the distribution of the electrical energy is uniform, and the ignition effect is well under this condition. So there is a best relationship in flow speed of the spray, size of the liquid droplet and the circumferential distribution of the spark energy.
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
2010年第10期1793-1796,共4页
Journal of Engineering Thermophysics
基金
国家自然科学基金资助项目(No.50776048)
关键词
液体推进剂
喷雾
电点火
瞬态测量
liquid propellant
spray
electrical ignition
transient measurement
