| 减压阀节流口流场仿真和分析 |
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| 引用本文： | 王定军,宋会玲,白少卿,魏超.减压阀节流口流场仿真和分析[J].火箭推进,2009,35(6):37-40,46. |
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| 作者姓名： | 王定军 宋会玲 白少卿 魏超 |
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| 作者单位： | 1. 西安航天动力研究所,陕西,西安710100
2. 西安航天发动机厂,陕西,西安710100 |
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| 摘 要： | 采用Fluent软件对火箭姿态控制系统减压阀环形节流口流场进行了数值仿真，得到了流场有关参数图形。减压阀节流口气体流场为非自由、紊动、冲击、壁面射流，气体在节流口达到音速，贴壁面高速射流出去后，相互撞击、压缩并撞击阀芯柱面产生激波，气流总压损失较大，建议采用等温过程进行特性计算。减压阀环形节流口后流场存在激波，总压并不守恒，目前通用的气流稳态流动力计算公式并不合适，应借助流场分析工具进行节流元件受力分析。
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| 关 键 词： | 姿态控制系统 节流口 流场 仿真 |
Simulation and analysis of the regulator orifice flow field |
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| Wang Dingjun,Song Huiling,Bai Shaoqing,Wei Chao.Simulation and analysis of the regulator orifice flow field[J].Journal of Rocket Propulsion,2009,35(6):37-40,46. |
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| Authors: | Wang Dingjun Song Huiling Bai Shaoqing Wei Chao |
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| Institution: | 1 Xi＇an Aerospace Propulsion Institute, Xi＇an 710100, China; 2 Xi＇an Space Engine Factory, Xi＇an 710100, China) |
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| Abstract: | Numerical simulation of flow field through an attitude control system regulator orifice is conducted with FLUENT. Transformation of flow field parameters shows that the flow is restricted, turbulent, impact flow against the wall. The gas flow is pressed against the wall and is rapidly shot out with sonic velocity. There produces shock wave in the compressed flow. Formula for isothermal flow is recommended for great total lose. Because of the existing of shock wave, total pressure varies with gas flowing through regulator orifice. Kinetic equations for steady flow can not be used to explain this process and CFD software is used to analyze this complex turbulent flow field. |
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| Keywords: | attitude control system regulator orifice flow field numerical simulation |
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