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底部结构对塞式喷管性能的影响
引用本文:戴梧叶,刘宇,张正科.底部结构对塞式喷管性能的影响[J].宇航学报,2002,23(2):34-40.
作者姓名:戴梧叶  刘宇  张正科
作者单位:北京航空航天大学宇航学院,北京,100083
基金项目:国家 8 63-2高技术航天领域 [863-2 -3-4 -10 ],国家自然科学基金资助项目 [5 97860 0 1]
摘    要:为了提高塞式喷管性能,特别是提高塞式喷管底部的作用,从降低逆压梯度出发,利用外形设计法提出了六种不同于传统平面底部的底部模型,并利用数值模拟对其进行了研究,简单介绍了控制塞锥底部分离流动的基本思路,数值方法采用二阶精度的NND格式NS方程,研究表明,这几种模型相对于传统底部模型而言,底部旋涡得到了较好的控制,底部的压强有明显的上升,塞式喷管性能得到了改善,性能甚至比加入二次流要好。而且外形设计法还不需要辅助设备和消耗额外的功率,是一个容易实现的方法,本文的模型6是一种不错的底部模型,把外形设计法和底部二次流结合起来使用会获得更好的性能,塞式喷管底部的潜力尚有很大的空间可以挖掘。

关 键 词:塞式喷管  数值模拟  火箭发动机  外形设计法  分离流动  影响
文章编号:1000-1328(2002)02-0034-07
修稿时间:2001年3月5日

Effect of base contour on aerospike nozzle performance
DAI Wu ye,LIU Yu,ZHANG Zheng ke.Effect of base contour on aerospike nozzle performance[J].Journal of Astronautics,2002,23(2):34-40.
Authors:DAI Wu ye  LIU Yu  ZHANG Zheng ke
Abstract:To improve the aerospike nozzle performance,especially to make good use of the aerospike nozzle base,based on reducing reverse pressure gradient and Contour Design Method (CDM),six aerospike nozzle base models that are different from the conditional planar base are introduced,and numerical study on these bases is completed.The idea of controlling the separated flow in the base is presented.The numerical method is based on N S equations with Second order NND scheme.The results indicate that for these base models,the base pressure is higher than the traditional planar base,so is the aerospike nozzle performance.The improvement of the aerospike nozzle performance produced by changing base contour is more than that produced by adding base bleed.The CDM presented in this paper,which don't need auxiliary facility and additional power,is easy to be put to use.The model 6 presented in this paper is attractive to be employed in aerospike nozzle.A more high performance is gotten if the bleed is added to the modified base.It suggests the base is potential to improve the aerospike nozzle performance.
Keywords:Aerospike nozzle  Numerical simulation  Rocket engines  Contour design method  Separated flow
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