| 可燃喷管固体发动机性能初探 |
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| 引用本文： | 方丁酉.可燃喷管固体发动机性能初探[J].固体火箭技术,1992(1):1-6. |
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| 作者姓名： | 方丁酉 |
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| 作者单位： | 国防科学技术大学 湖南长沙 |
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| 摘 要： | 可燃喷管固体火箭发动机具有成本低、可靠性高等优点,可用作运载火箭助推器,本文对它的性能进行了初步探索。理论计算的内弹道曲线及喷管型面与实验结果基本一致,实验结果表明,该发动机的比冲稍低于钢喷管发动机的比冲;喷喉圆柱段的燃速比收敛段和扩散段的燃速高,燃烧规律也不相同。
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| 关 键 词： | 固体火箭 火箭发动机 喷管 |
PRELIMINARY EXPLORATION FOR PERFORMANCE OF THE SOLID ROCKET MOTOR WITH A COMBUSTIBLE NOZZLE |
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| Fang Dingyou National University of Defense Technology,Changsha,Hunan.PRELIMINARY EXPLORATION FOR PERFORMANCE OF THE SOLID ROCKET MOTOR WITH A COMBUSTIBLE NOZZLE[J].Journal of Solid Rocket Technology,1992(1):1-6. |
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| Authors: | Fang Dingyou National University of Defense Technology Changsha Hunan |
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| Institution: | Fang Dingyou National University of Defense Technology,Changsha,Hunan,410073 |
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| Abstract: | The solid rocket motor with a combustible nozzle, which can be used forthe booster of launching vehicles, has advantages of low cost and high reliability. Thepreliminary exploration for its performance is presented. The theoretically calculated in-ternal ballistic curve and nozzle contour essentially agree with the experimlntal results.The results show that the specific impulse of the motor is slightly lower than that of themotor with a steel nozzle, and the burning rate of the nozzlc throat cylinder is higherthan that of the convergent and divergent sections, with the different combustion regular-ities from each other. |
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| Keywords: | Solid rocket engine Rocket engine nozzle Interior ballistic calculation Nozzleless rocket engine Booster |
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