| 某型号固体火箭发动机喷管型面设计与数值计算 |
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| 引用本文： | 刘文芝,张乃仁,张春林,赵永忠.某型号固体火箭发动机喷管型面设计与数值计算[J].工程设计学报,2006,13(2):99-103. |
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| 作者姓名： | 刘文芝 张乃仁 张春林 赵永忠 |
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| 作者单位： | 1.北京理工大学 机械与车辆工程学院， 北京 100081； 2.中国航天科学工业集团公司 六院41所， 内蒙古 呼和浩特 010062 |
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| 摘 要： | 根据某型号固体火箭发动机总体设计要求及限制条件，给出了喷管型面设计方法。采用计算流体动力学(CFD)方法，用单方程（Spalart-Allmaras）湍流模型，分析计算了不同入口压力下喷管内流场特性和壁面压力、温度分布等。根据流场计算结果求出了发动机瞬时推力，并与地面推力试验结果进行了对比。
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| 关 键 词： | 固体火箭发动机 喷管型面 CFD 地面试验 |
| 文章编号： | 1006-754X（2006）02-0099-05 |
| 收稿时间： | 2005-07-04 |
| 修稿时间： | 2005-07-04 |
Contour design and numerical calculation of certain solid propellant rocket motor nozzle |
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| LIU Wen-zhi,ZHANG Nai-ren,ZHANG Chun-lin,ZHAO Yong-zhong.Contour design and numerical calculation of certain solid propellant rocket motor nozzle[J].Journal of Engineering Design,2006,13(2):99-103. |
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| Authors: | LIU Wen-zhi ZHANG Nai-ren ZHANG Chun-lin ZHAO Yong-zhong |
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| Affiliation: | 1. School of Mechanical and Vehicular Engineering, Beijing Institute of Technology, Beijing 100081, China; 2. The 41th Institute of the Sixth Academy of China Aerospace Science and Industry Corporation, Huhhot 010062, China |
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| Abstract: | According to the entire design requirements and restraints of a certain solid propellant rocket motor,design method of nozzle contour is put forward. In this method,muzzle internal flow field,pressure against nozzle wall and temperature variation under different pressures are analyzed by applying Computational Fluid Dynamics(CFD),one-equation model: S-A Turbulent Model and finite volume method.According the results of computation of flow field,instantaneous propulsion of motor is gained,which is compared to the result of ground test. |
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| Keywords: | CFD |
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