| 引用本文: | 焦继革,张为华,夏智勋,等.燃气流量可调固体火箭冲压发动机飞行性能分析.[J].国防科技大学学报,2011,33(1):21-24,43.[点击复制] |
| JIAO Jige,ZHANG Weihua,XIA Zhixun,et al.Flight Performance Analysis of Variable Flow Ducted Rocket[J].Journal of National University of Defense Technology,2011,33(1):21-24,43[点击复制] |
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| 燃气流量可调固体火箭冲压发动机飞行性能分析 |
| 焦继革, 张为华, 夏智勋, 胡建新, 马立坤 |
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(国防科技大学 航天与材料工程学院，湖南 长沙 410073)
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| 摘要: |
| 在建立燃气流量可调固体火箭冲压发动机工作过程仿真模型的基础上，对燃气流量调节过程中发动机飞行性能进行分析。结果表明，在低飞行高度或高飞
行马赫数时，发动机有较宽的推力调节范围；随着飞行高度降低或飞行马赫数增加，发动机推力系数降低；随着燃气发生器喷喉面积变小，发动机推力和推力系数增加。 |
| 关键词: 固体火箭冲压发动机 燃气流量可调 工作过程仿真 飞行性能 |
| DOI： |
| 投稿日期：2010-09-30 |
| 基金项目: |
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| Flight Performance Analysis of Variable Flow Ducted Rocket |
| JIAO Jige, ZHANG Weihua, XIA Zhixun, HU Jianxin, MA Likun |
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(College of Aerospace and Materials Engineering, National Univ. of Defense Technology, Changsha 410073, China)
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| Abstract: |
| Based on ducted rocket operating principle, mathematical working model of air inlet, gas generator and secondary chamber was built.
The altitude characteristics and velocity characteristics of variable flow ducted rocket were numerically studied. Increasing the flight mach or decreasing the flight altitude can not only help the engine work in a wide range of thrust, but also decrease the thrust coefficient. Decreasing the area of gas regulation valve can increase thrust and thrust coefficient |
| Keywords: ducted rocket variable flow operation process flight performance |
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