摘要
Flying aerodynamic heating makes great effect on the reliability of nose fuze. The computational model of air boundary layer of rocket fuze was established. Considering different material characteristics, correlative mathematic model was built by finite element analysis. The simulation was conducted by Fluent software. The simulation results show that the method possesses high accuracy and lays the foundation for thermal supervision of nose fuze.
| 源语言 | 英语 |
|---|---|
| 页（从-至） | 406-410 |
| 页数 | 5 |
| 期刊 | Binggong Xuebao/Acta Armamentarii |
| 卷 | 28 |
| 期 | 4 |
| 出版状态 | 已出版 - 4月 2007 |
指纹
探究 'Numerical simulation method for thermal characteristic of air boundary layer of rocket fuze' 的科研主题。它们共同构成独一无二的指纹。引用此
Lou, W. Z., & Qi, B. (2007). Numerical simulation method for thermal characteristic of air boundary layer of rocket fuze. Binggong Xuebao/Acta Armamentarii, 28(4), 406-410.