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固体火箭超燃冲压发动机模态转换迟滞现象研究-金属燃料推进剂技术专栏

董新刚1,蔡瑞鹏2,杨玉新3,黄礼铿2,何国强4   

  1. 1. 西北工业大学航天学院
    2. 西安航天动力技术研究所
    3. 西安航天动力技术研究
    4. 西北工业大学
  • 收稿日期:2025-10-24 修回日期:2026-01-09 出版日期:2026-01-15 发布日期:2026-01-15
  • 通讯作者: 黄礼铿

Hysteresis of combustion mode transition in solid rocket scramjet engine

  • Received:2025-10-24 Revised:2026-01-09 Online:2026-01-15 Published:2026-01-15
  • Contact: Li-Keng HUANG

摘要: 为了提高对固体火箭超燃冲压发动机中模态转换特性的认识水平,本文开展了固体火箭超燃冲压发动机模态转换直连试验研究。试验结果显示,在相同的工作参数和发动机构型下,燃烧室可能处于超燃模态也可能处于亚燃模态,即存在模态转换迟滞现象。通过分析直连试验点火初始阶段发动机的沿程压强分布,发现燃烧模态迟滞现象是一次燃气着火区域的不同造成的。

关键词: 固体火箭, 超燃冲压, 模态转换, 迟滞现象, 直连试验

Abstract: To raise the level of understanding of combustion mode transition characteristics in solid rocket scramjet engine, direct connect experiment of mode transition in solid rocket scramjet engine is investigated in this paper. The result shows that under the same inlet flow condition and engine configuration, there may be subsonic combustion mode or supersonic combustion mode, and in other words, hysteresis of combustion mode transition appears. Analyzing the distribution of pressure along the engine during initial ignition stage of experiments, it is found that hysteresis of combustion mode transition is caused by difference in ignition region of fuel gas.

Key words: Solid rocket, Scramjet, Mode transition, Hysteresis, Direct connect experiment

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