航天推进技术研究院主办
[1]梁俊龙,吴宝元,李斌.几何结构可调的亚燃冲压发动机性能研究[J].火箭推进,2010,36(02):1-4.
Liang Junlong,Wu Baoyuan,Li Bin.Performance research of adjustable geometric structure ramjet engine[J].Journal of Rocket Propulsion,2010,36(02):1-4.
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Liang Junlong,Wu Baoyuan,Li Bin.Performance research of adjustable geometric structure ramjet engine[J].Journal of Rocket Propulsion,2010,36(02):1-4.
几何结构可调的亚燃冲压发动机性能研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
36
期数:
2010年02期
页码:
1-4
栏目:
研究与设计
出版日期:
2010-04-15
- Title:
- Performance research of adjustable geometric structure ramjet engine
- 文章编号:
- (2010)02-0001-0５
- 分类号:
- V434
- 文献标志码:
- A
- 摘要:
- 液体亚燃冲压发动机结构简单、推重比高，是高动态临近空间飞行器的最佳动力装置，临近空间飞行器的飞行速度范围宽、距离远，亟需采用几何结构可调技术来提高冲压发动机的性能。本研究对具有固定、连续可调进气道和尾喷管的冲压发动机性能进行了计算和比较。结果表明，采用连续可调喷管的冲压发动机的性能大大优于固定几何结构的冲压发动机，进气道可调带来的冲压发动机性能增加远小于喷管连续可调带来的发动机性能增加。
- Abstract:
- Simple structure and high specific impulse liquid ramjet is the best engine concept of high dynamic vehicles near space. The vehicles with large flight velocity range and long flight distance near space require high performance ramjets that adopt adjustable geometric structure technology. The ramjet performance is calculated and compared with fixed and continuous adjustable structure intake and nozzle in this paper. The results show that the performance of a ramjet with continuous adjustable nozzle is much better than a ramjet with fixed structure. Improved ramjet performance from adjustable intake is much lower than improved performance from continuous adjustable nozzle.
备注/Memo
收稿日期：200９-０9-22；修回日期：200９-12-03。
作者简介： 梁俊龙（1977—），男，硕士，研究领域为冲压发动机系统设计。
更新日期/Last Update:
1900-01-01