| 锥型喷管总温、总压分布不均匀对推力偏心的影响 |
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| 引用本文： | 徐志明,周建伟,武晓松,欧阳宏斌.锥型喷管总温、总压分布不均匀对推力偏心的影响[J].弹道学报,1999(2). |
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| 作者姓名： | 徐志明 周建伟 武晓松 欧阳宏斌 |
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| 作者单位： | 上海交通大学机电控制研究所!上海200030(徐志明)，南京理工大学动力工程学院(周建伟)，南京理工大学机械学院(武晓松)，南京理工大学理学院!南京210094(欧阳宏斌) |
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| 摘 要： | 用特征面参数化方法数值模拟了喷管的非对称流场，研究了当总温、总压在喷管超声速段入口截面分布不均匀时，所引起的锥型喷管的推力偏心特性，得到了锥型喷管在不同扩张角和不同总温、总压分布时，喷管侧向推力分量沿轴向的变化及其零点位置在轴线上的分布规律．对微推偏喷管的设计具有重要参考价值．
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| 关 键 词： | 火箭发动机 特征线法 数值模拟 锥型喷管 |
THE EFFECTS OF THE STAGNATION TEMPERATURE AND STAGNATION PRESSURE'S NON SYMMETRICAL DISTRIBUTION ON THE THRUST MISALIGNMENT OF CONICAL NOZZLE |
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| Abstract: | In this paper, the isentropic, non symmetrical flow fields in nozzle are numerically simulated by three dimensional method of characteristics. The thrust misalignment in rocket nozzle is investigated for the situation where the stagnation temperature and stagnation pressure are disturbed non symmetrically in the supersonic region of the nozzle. Distributions of side force and zero points along the axis of nozzle are presented for different distribution of stagnation temperature and stagnation pressure of conical nozzles. |
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| Keywords: | rocket engine nozzle characteristic method numerical simulation conical nozzle |
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