摘要
为了预示导弹地下发射井中的噪声环境、检验某型多孔吸声材料的实际吸声效果,通过缩比模型试验进行了验证和仿真。按照缩比原则设计了缩小比例为1∶10的模型发动机,采用网格计算方法对缩比模型和原型发动机之间的温度场、速度场和压力场进行了定常仿真分析与比较。结果表明,缩比试验的结果与井下原型导弹的射流流场具有可比性,试验测量数据可以作为评价吸声材料的实际应用效果。对缩比模型的设计过程进行了研究。通过对模型发动机流场和原型发动机流场的仿真和比较,验证了缩比试验技术方案的合理性。
To forecast the noise environment during launch process and validate the efficiency of noise reduction technique, a small proportion trial model of rocket engine scaled 1： 10 is designed and validated by numerical simulation. The method of grid numeration is adopted to compare the fluid of temperature, velocity and pressure between the model and actual silo missile fluid. The result proved the feasibility of using small proportional model to compare the actual fluid of missile. During the design of noise absorption material, the process of model design and result of launch trial are given in this paper.
出处
《计算机仿真》
CSCD
2008年第8期51-54,共4页
Computer Simulation
关键词
噪声
地下井
模型
仿真
缩比模型
Noise
Silo
Model
Simulation
Small proportion model
