| 摘要: |
| 应用脉冲枪不稳定燃烧模型对有 /无声腔的MMH/NTO火箭发动机的燃烧稳定性进行了数值模拟 ,比较了 3台MMH/NTO发动机的燃烧动态稳定性 ,计算与发动机的试车结果一致。 |
| 关键词: 流动推进剂火箭发动机 燃烧稳定性 脉冲枪模型 数值仿真 数值分析 |
| DOI： |
| 分类号:V434.13 |
| 基金项目:国家“八六三”基金资助项目 |
|
| Numerical assessment of MMH/NTO rocket engine combustion instability |
|
ZHUANG Feng-chen1, ZHANG Zhong-guang2, NIE Wan-sheng1, NIE Wan-sheng1
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1.Inst. of Equipment Command and Technology, Beijing 101400,China;2.Shanghai Inst.of Power Machinery, Shanghai 200233,China
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| Abstract: |
| A given MMH/NTO rocket engine combustion stability with/without acoustic cavities was numerically simulated by pulse gun combustion instability model.Three MMH/NTO rocket engines combustion dynamic stabilities were compared and assessed. Numerical simulation and assessment results are agreeable with the engine hot test data. |
| Key words: Liquid propellant rocket engine Combustion stability Pulse gun model Numerical simulation Numerical analycis |
