高超声速飞行器推进模块的设计参数分析

曹德一; 李椿萱

高超声速飞行器推进模块的设计参数分析

北京航空航天大学航空科学与工程学院, 北京 100083

基金项目: 航天科技创新基金

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出版历程
- 收稿日期: 2007-08-09
- 修回日期: 2007-12-17
- 刊出日期: 2008-07-28

Parametric analysis of an integrated airframe/propulsion module design for hypersonic vehicle

School of Aeronautical Sciences and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

摘要

摘要: 通过斜激波理论、准一维工程估算和特征线方法建立了一个与飞行器机体一体化的推进系统模块的气动分析模型,其中采用参考温度法估算模块的粘性效应。在此基础上分别研究了飞行器前体长度、前缘角及推进模块宽度等关键设计参数对推进模块气动性能的影响。结果表明:增大模块前体长度将使模块的升力、净推力和比冲先增后降;增加前缘角将增加升力,但降低净推力;增加模块宽度会导致等效升力下降。因此,在设计此类高超声速巡航飞行器时,应采用模块化的推进系统并折衷选择前体长度和前缘角的大小。
- 高超声速 /
- 一体化设计 /
- 参数研究
Abstract: An aerodynamic analysis model for an airframe/propulsion integrated module was established based the theory of oblique-shock,in conjunction with a quasi～-1Dengineering estimation and the method of characteristics.The viscosity effects of the module were taken into account using the method of reference temperature.Aparametric analysis was then performed using the developed model.The influences of the design parameters,including the fore-body length,the leading angle,and the width of the module upon the aerodynamic characteristics were presented.The results reveal that increasing the length of the fore-body will make the thrust and the lift,as well as the specific impulse of the module to increase first and then decrease;increasing the leading angle will increase the lift but decrease the thrust;increasing the width of the module will decrease the equivalence lift.Hence,modularized propulsion system and the trade-off among these variables must be taken into account in the configuration design of the hypersonic cruise vehicle.
- hypersonic /
- integrated design /
- parametric study

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参考文献(16)

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