| 固体火箭发动机液体喷射熄火液量的确定 |
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| 引用本文： | 殷金其,王克秀,吴心平.固体火箭发动机液体喷射熄火液量的确定[J].航空动力学报,1993,8(3):255-258,308. |
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| 作者姓名： | 殷金其 王克秀 吴心平 |
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| 作者单位： | 西安市西北工业大学802教研室，西北工业大学，西北工业大学 710072 |
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| 摘 要： | 本文运用固体火箭发动机液体喷射熄火模型 ,确定了液体喷射熄火液量 ,研究了推进剂能量、压强指数、燃烧室压强、液体性质和喷射压降等多种因素的影响。
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| 关 键 词： | 固体火箭发动机 液体喷射熄火 熄火液量 理论模型 |
| 收稿时间： | 9/1/1992 12:00:00 AM |
DETERMINATION OF LIQUID QUANTITY REQUIRED FOR LIQUID QUENCH OF SOLID ROCKET MOTOR |
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| Yin Jinqi,Wang Kexiu and Wu Xinping.DETERMINATION OF LIQUID QUANTITY REQUIRED FOR LIQUID QUENCH OF SOLID ROCKET MOTOR[J].Journal of Aerospace Power,1993,8(3):255-258,308. |
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| Authors: | Yin Jinqi Wang Kexiu and Wu Xinping |
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| Institution: | Northwestern Polytechnical University;Northwestern Polytechnical University;Northwestern Polytechnical University |
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| Abstract: | The liquid quantity required(LQR)for liquid quench of solid rocket motor was determined with the use of a theoretical model developed by the authors.LQR increases with propellant energy and decreases as the evaporation heat of liquid and the liquid pressure drop(the difference between injection pressure of liquid and chamber pressure)increase.The effects of the chamber pressure and burning rate pressure exponent of propellant on LQR merge into the effect of mass burning rate of propellant.Then LQR increases with increasing mass burning rate.The theoretical results are in good agreement with experimental data. |
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