| 飞行状态下脉冲爆震发动机性能估计分析 |
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| 引用本文： | 邱华,严传俊,范玮,黄希桥,张群,郑龙席,熊姹.飞行状态下脉冲爆震发动机性能估计分析[J].航空动力学报,2004,19(5):656-659. |
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| 作者姓名： | 邱华 严传俊 范玮 黄希桥 张群 郑龙席 熊姹 |
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| 作者单位： | 西北工业大学,动力与能源学院,陕西,西安,710072 |
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| 基金项目： | 国家自然科学基金资助项目(50336030)，西北工业大学博士创新基金资助项目(CX200316) |
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| 摘 要： | 在理想单循环脉冲爆震发动机分析模型的基础上,通过引入进气道建立了一定飞行状态下的自吸气的脉冲爆震发动机理论性能计算模型,研究了当飞行状态改变时,脉冲爆震发动机的性能变化趋势,计算结果表明,对给定模型,飞行高度和飞行马赫数对脉冲爆震发动机性能的影响是不一样的,决定于进气道和爆震室的推进特性,同时模型也考虑了爆震频率和爆震室直径对性能的影响,这为脉冲爆震发动机的理论设计和分析提供了一定依据。
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| 关 键 词： | 航空、航天推进系统 脉冲爆震发动机 自吸气 性能 |
| 文章编号： | 1000-8055(2004)05-0656-04 |
| 收稿时间： | 2003/11/16 0:00:00 |
| 修稿时间： | 2003年11月16 |
Assessment Analysis of Pulse Detonation Engine Performance in Flight Regime |
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| QIU Hu,YAN Chuan-jun,FAN Wei,HUANG Xi-qiao,ZHANG Qun,ZHENG Long-xi and XIONG Cha.Assessment Analysis of Pulse Detonation Engine Performance in Flight Regime[J].Journal of Aerospace Power,2004,19(5):656-659. |
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| Authors: | QIU Hu YAN Chuan-jun FAN Wei HUANG Xi-qiao ZHANG Qun ZHENG Long-xi and XIONG Cha |
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| Institution: | School of Dynamics and Energy,Northwestern Polytechnical University,Xi'an710072,China;School of Dynamics and Energy,Northwestern Polytechnical University,Xi'an710072,China;School of Dynamics and Energy,Northwestern Polytechnical University,Xi'an710072,China;School of Dynamics and Energy,Northwestern Polytechnical University,Xi'an710072,China;School of Dynamics and Energy,Northwestern Polytechnical University,Xi'an710072,China;School of Dynamics and Energy,Northwestern Polytechnical University,Xi'an710072,China;School of Dynamics and Energy,Northwestern Polytechnical University,Xi'an710072,China |
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| Abstract: | A theoretical performance analysis model of air-breathing pulse detonation engine is established in the flight regimes.It is based on single-cycle pulse detonation engine analysis model.The influence of the flight regime change on performance of pulse detonation engine was studied.The results show that the average thrust is decreased with the increase of flight altitude at given Mach number, and the influence of Mach number on thrust depends on the propulsive characteristics of inlet and detonation chamber.The effect of detonation frequency and combustor diameter is also considered in the model which is useful to the design and analysis of pulse detonation engine. |
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| Keywords: | aerospace propulsion system pulse detonation engine air-breathing performance |
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