| 大长径比固体火箭发动机点火瞬态过程分析 |
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| 引用本文： | 钟涛,王中伟,张为华.大长径比固体火箭发动机点火瞬态过程分析[J].固体火箭技术,2005,28(1):20-22,64. |
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| 作者姓名： | 钟涛 王中伟 张为华 |
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| 作者单位： | 国防科技大学航天与材料工程学院,长沙,410073;国防科技大学航天与材料工程学院,长沙,410073;国防科技大学航天与材料工程学院,长沙,410073 |
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| 基金项目： | 国家 863高新技术项目资助(2002AA765030)。 |
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| 摘 要： | 为了定量描述大长径比固体火箭发动机点火滞后期和火焰传播过程，分析了试验压强一时间曲线和升压速率曲线，并利用数值计算对点火瞬态过程进行仿真；根据两条曲线的数学与物理意义推断主装药首次火焰时刻为升压速率上升阶段过零时刻，火焰传播结束时刻为升压速率由上升转下降的极值时刻；数值仿真结果验证了这一推断。该方法简单有效，适用于工程实践。
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| 关 键 词： | 固体推进剂火箭发动机 点火瞬态过程 升压速率 首次火焰 火焰传播 |
| 文章编号： | 1006-2793(2005)01-0020-03 |
Analysis of ignition transient for large aspect ratio solid rocket motors |
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| Zhong Tao,WANG Zhong-wei,ZHANG Wei-hua.Analysis of ignition transient for large aspect ratio solid rocket motors[J].Journal of Solid Rocket Technology,2005,28(1):20-22,64. |
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| Authors: | Zhong Tao WANG Zhong-wei ZHANG Wei-hua |
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| Institution: | ZHONG Tao,WANG Zhong-wei,ZHANG Wei-huaCollege of Aerospace and Material Engineering,National Univ. of Defense Technology,Changsha 410073,China. |
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| Abstract: | In order to quantitatively describe ignition lag and flame propagation in large aspect ratio SRMs, the pressure vs time curve and pressure-rise velocity curve were analyzed. Ignition transient were numerically simulated. Based on mathematic and physical meanings of the curves, the first flame time of sustaining grain was deduced as zero time of rise stage for pressure-rise velocity and the end time of flame propagation as the limit time from rise to drop. The results of simulation verified the deduction. The method is simple valid, and suitable for engineering practice. |
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| Keywords: | solid propellant rocket engine ignition transient pressure velocity the first flame flame transmittal |
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