| 运载火箭可延伸喷管比冲增益的折合算法 |
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| 引用本文： | 马国宝.运载火箭可延伸喷管比冲增益的折合算法[J].宇航学报,1996,17(1):81-86. |
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| 作者姓名： | 马国宝 |
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| 作者单位： | 航天四院四十一所 |
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| 摘 要： | 本文在多级火箭理想末速度公式的基础上，推导了可延伸喷管有效比冲增益的计算公式，并对某三级固体运载火箭进行计算，得到了三种状态下可延伸喷管的有效比冲增益
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| 关 键 词： | 喷管可延伸喷管 固体火箭发动机 比冲 |
THE CONVERTING CALCULATION METHOD OF THE SPECIFIC IMPULSE FOR THE EXTENDIBLE EXIT CONE OF THE LAUNCHING VEHICLE |
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| Ma Guobao.THE CONVERTING CALCULATION METHOD OF THE SPECIFIC IMPULSE FOR THE EXTENDIBLE EXIT CONE OF THE LAUNCHING VEHICLE[J].Journal of Astronautics,1996,17(1):81-86. |
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| Authors: | Ma Guobao |
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| Abstract: | A calculation method is prsented to determine the effective gain of specific impulse,when the extendible exit cones(cone)are(is)used in upper stages(stage)of the launching vehicle. The formulations of this method are developed by the ideal velocity eguations of multistage rocket. A certain solid rocket motor missile is analysised by this calculation method. The effective specific impulse gains of the extendible exit cones(cone)are calculated under three conditions. |
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| Keywords: | Nozzle Extendible exit cone Solid rocket Specific impulse |
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