摘要
模拟固体火箭发动机是真实火箭发动机按一定比例缩小的试验装置,与真实火箭发动机比较,其喷流温度和速度都略低,但温度仍高达1500～2500°K,速度达1300～2500m/s,持续时间为1～3s。流动是高亮度含有大量熔化粒子的两相流动。因此这项测量具有背景噪声高、时间短和流速极高的特点。对于管道中这种流动的测量除上述特点外。
This paper describes the velocity measurements of the jet flows from a model of solid-propellant rocket engines using a LDV system. To extend the range of velocity measurement, a large pre-set frequency shift is used. Various filtering techniques are used to restrain the effects of the strong background noises.Windows are installed along the pipe for measuring the flow in the pipe, and special window supports are designed to protect the windows from burn out. In addition,the limitation for selecting the countering-cycle numbering adopted by the counter type signal processor, due to the presence of the reverse pre-set frequency shift, is discussed.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1989年第10期B521-B525,共5页
Acta Aeronautica et Astronautica Sinica
关键词
火箭发动机
固体火箭
喷流
流速
model test, solid-propellent rocket engine, laser anemometer.
