| 水下固体火箭发动机尾流场计算 |
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| 引用本文： | 王建儒,赵仕厂.水下固体火箭发动机尾流场计算[J].固体火箭技术,2007,30(5):388-391. |
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| 作者姓名： | 王建儒 赵仕厂 |
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| 作者单位： | 1. 西北工业大学航天学院,西安,710072
2. 中国航天科技集团公司四院四十一所,西安,710025 |
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| 摘 要： | 采用了二维定常气流场模型和轴对称理想水流场模型,对水下工作固体火箭发动机尾流场进行了耦合数值求解。考虑了高温燃气与水介质之间传热、汽化等对内部气体流动的影响,数值模拟了尾流场中压强、温度在发动机尾流场中沿轴向、径向的分布规律和特征及参数变动对喷管性能的影响,所获得的流场压强、温度分布规律可为水下工作固体发动机设计提供依据。
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| 关 键 词： | 固体火箭发动机 尾流场 耦合 |
| 文章编号： | 1006-2793（2007）05-0388-04 |
| 收稿时间： | 2006-08-03 |
| 修稿时间： | 2007-04-28 |
Computations for solid rocket moter tail flow under water |
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| WANG Jian-ru,ZHAO Shi-chang.Computations for solid rocket moter tail flow under water[J].Journal of Solid Rocket Technology,2007,30(5):388-391. |
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| Authors: | WANG Jian-ru ZHAO Shi-chang |
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| Abstract: | The coupling numerical value for SRM tail flow under water was calculated by means of 2D compressible gas-phase flow model and incompressible liquid-phase flow model.Heat conductivity of high temperature gas and water,vapor phenomenon of high temperature water were introduced to simulate distribution rule of pressure,temperature along axial and radial direction.The influence of parameters change on nozzle performance was studied.The obtained distribution rule of pressure and temperature provides good basis for design of underwater SRM. |
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| Keywords: | solid rocket motor tail flows coupling |
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