| 模拟固体火箭发动机喷流流速测量 |
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| 引用本文： | 张孝棣,贾元胜,曹锐,唐敏中.模拟固体火箭发动机喷流流速测量[J].航空学报,1989,10(10):526-529. |
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| 作者姓名： | 张孝棣 贾元胜 曹锐 唐敏中 |
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| 作者单位： | 哈尔滨空气动力研究所
(张孝棣，贾元胜，曹锐)，哈尔滨空气动力研究所(唐敏中) |
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| 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,还需解决窗口烧
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| 关 键 词： | 模型实验 固体火箭发动机 激光风速计 |
| 收稿时间： | 1988-02-26; |
VELOCITY MEASUREMENT OF THE MODEL SOLID ROCKET ENGINES JET FLOW |
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| Harbin Aerodynamics Research Institute Zhang Xiaodi,Jia Yuansheng,Chao Rui and Tang Minzhong.VELOCITY MEASUREMENT OF THE MODEL SOLID ROCKET ENGINES JET FLOW[J].Acta Aeronautica et Astronautica Sinica,1989,10(10):526-529. |
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| Authors: | Harbin Aerodynamics Research Institute Zhang Xiaodi Jia Yuansheng Chao Rui and Tang Minzhong |
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| Institution: | Harbin Aerodynamics Research Institute |
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| Abstract: | 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. |
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| Keywords: | model test solid-propellent rocket engine laser anemometer |
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