摘要
采用二维开窗式固体火箭冲压发动机试验系统,对补燃室内的燃烧现象进行观察,以火焰图像的形式直观形象地描述了进气道位置对补燃室内燃烧过程的影响,试验所采用的装药为含硼贫氧推进剂。并通过高速数字摄影仪摄取补燃室内部某个时刻瞬时火焰图像,借助于光学理论和计算机图像处理技术计算出整个补燃室内部的温度分布。
In order to get better insight in the combustion behavior of the secondary combustion chambers, a high-speed photography has been used to analyze the highly turbulent multiphase combustion flow. During the test, boron-based fuel-rich HTPB propellant is used. The portion of the primary plume is viewed through a quartz window and is recorded by photography. The geometry has been designed with a square section for the duct to facilitate optical access inside the combustor. Rebuild the combustion flame＇ s temperature field by applying the digital image processing technology.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2007年第4期337-341,共5页
Journal of Propulsion Technology
基金
国家自然科学基金(50376072)
关键词
固体火箭冲压发动机
补燃室
含硼推进剂
燃烧试验
温度测量
图像处理
Ducted rocket
Secondary combustion chamber
Boron-based propellant
Combustion experiment
Temperature measurement
Digital image processing
