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塞式喷管推力模型的建立与实验验证
引用本文:琚春光,刘宇.塞式喷管推力模型的建立与实验验证[J].航空学报,2007,28(4):821-826.
作者姓名:琚春光  刘宇
作者单位:北京航空航天大学,宇航学院,北京,100083
摘    要: 为了能够方便快捷地对塞式喷管发动机的性能做出准确的预示,通过理论分析,结合塞式喷管的流场特征,提出了一种塞式喷管壁面压强分布的数学模型。在此基础上,分别建立了全长型和截短型的塞式喷管的推力模型。通过与实验的对比分析,模型与实验数据基本吻合,验证了塞式壁面压力分布的数学模型以及在此基础上建立的推力模型,可以作为塞式喷管发动机性能预示的有效工具。

关 键 词:火箭发动机  塞式喷管  推力系数  
文章编号:1000-6893(2007)04-0821-06
修稿时间:2006年11月15

Establishment and Experiment Comparison of Thrust Models for Plug Nozzle
JU Chun-guang,LIU Yu.Establishment and Experiment Comparison of Thrust Models for Plug Nozzle[J].Acta Aeronautica et Astronautica Sinica,2007,28(4):821-826.
Authors:JU Chun-guang  LIU Yu
Institution:School of Astronautics, Beijing University of Aeronautics and Astronautics
Abstract:In order to obtain the thrust performances of plug nozzles rapidly and correctly,a mathematical model of the pressure distribution on plug wall is established by theoretical analysis with combination of the flow phenomena in plug nozzles.Based on the mathematical model,thrust models for the plug nozzle with full length and truncated central body are established.Through comparison and analysis,the results got from the model are quite consistent with experiment results,implying that the mathematical model of pressure distribution and the thrust models are effective and can work as effective tools in the performance evaluation of plug nozzles.
Keywords:rocket engine  plug nozzle  thrust coefficient
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