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火箭射流
相关语句
  rocket jet
     EXPERIMENTAL STUDIES ON SHOCK WAVE STRUCTURES IN THE IMPINGEMENT OF THE REAL ROCKET JET
     真实火箭射流冲击流场中激波结构的实验研究
短句来源
     So the problem of taking the picture of real rocket jet with high temperature, high velocity and strong flame was solved.
     解决了长期以来无法拍摄到高温、高速、强火焰光的火箭射流流场图像的问题。
短句来源
     So the problem of taking the picture of real rocket jet flow field with high temperature, high valocity, strong vibration and strong flame are solved.
     解决了长期以来无法拍摄到高温、高速、强振动冲击、强火焰光的火箭射流流场图像问题.
短句来源
  rocket exhaust plumes
     COMPUTATION ON SHOCK STRUCTURES OF THE ROCKET EXHAUST PLUMES
     火箭射流激波系的计算
短句来源
  real rocket jet
     EXPERIMENTAL STUDIES ON SHOCK WAVE STRUCTURES IN THE IMPINGEMENT OF THE REAL ROCKET JET
     真实火箭射流冲击流场中激波结构的实验研究
短句来源
     So the problem of taking the picture of real rocket jet with high temperature, high velocity and strong flame was solved.
     解决了长期以来无法拍摄到高温、高速、强火焰光的火箭射流流场图像的问题。
短句来源
     So the problem of taking the picture of real rocket jet flow field with high temperature, high valocity, strong vibration and strong flame are solved.
     解决了长期以来无法拍摄到高温、高速、强振动冲击、强火焰光的火箭射流流场图像问题.
短句来源
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  rocket exhaust plumes
A three-dimensional model of radiation of rocket exhaust plumes is given, which is based on the Monte Carlo simulation method.
      
The results are given of calculations of the spectral and integral emissivity of light-scattering rocket exhaust plumes of various configurations, containing Al2O3 particles with an average radius of 2 μm, in the infrared spectral region of 2-5 μm.
      
A simple entrainment model is used to estimate droplet streamlines, velocity and mass flux in rocket exhaust plumes.
      


In this paper, the pictures of shock wave structures in the flow field of real rocket jet impingement were gotten by a very effective Laser-Moire interference system. So the problem of taking the picture of real rocket jet with high temperature, high velocity and strong flame was solved. Using this system, we studied jet impinging cone and found some new shock wave structures.

本文采用一种有效的激光-莫瑞光栅干涉系统首次拍摄到真实火箭燃气射流冲击流场的激波结构.解决了长期以来无法拍摄到高温、高速、强火焰光的火箭射流流场图像的问题。利用这一系统,研究了射流冲击流场中激波结构的一些变化规律,发现了一些新的激波结构。较系统地研究了欠膨胀射流冲击各种锥体的激波形态。

The measurement principle of coherent moire deflectometry with filter is analyzed theoretically by using Fourier optical method. It is used to study the experiment of impingement flow field of real rocket exhausted jet. The moire deflectograms of impingement flow field of real rocket exhausted jet are obtained. So the problem of taking the picture of real rocket jet flow field with high temperature, high valocity, strong vibration and strong flame are solved.

用傅里叶光学方法从理论上分析了带有滤波器的相干性莫尔偏折法的测量原理,把这种方法用于真实火箭燃气射流冲击场的实验研究.获得了真实火箭燃气射流冲击流场莫尔偏折图.解决了长期以来无法拍摄到高温、高速、强振动冲击、强火焰光的火箭射流流场图像问题.

In this paper,Moire stripe displacement on shock wave resulting from real rocket exhausted plume have been clearly visualized by used of Laser-Moire deflectometry and auto-measuring pressure system.the results of density distribution on under-expanded rocket exhausted plume have been firstly obtained. The result fairly agree with the theory of exhausted plume.

本文采用用激光-莫尔偏折和自动测压系统,清晰地显示出真实火箭燃气射流场在激波处的莫尔条纹漂移,首次定量地给出了一种欠膨胀火箭射流的密度分布结果,该结果与射流理论符合较好。

 
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