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| Contour design and numerical calculation of certain solid propellant rocket motor nozzle |
| LIU Wen-Zhi1, ZHANG Nai-Ren1, ZHANG Chun-Lin1, ZHAO Yong-Zhong2 |
| 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 finitevolume 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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Published: 28 April 2006
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某型号固体火箭发动机喷管型面设计与数值计算
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。
关键词：
固体火箭发动机,
喷管型面,
CFD,
地面试验
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