摘要
对一种独立模块薄壳进气道开展了气动变形对其性能影响的数值计算研究,获得了不同反压、不同工作高度、不同来流马赫数及不同壁厚下进气道型面的变形结果及变形前/后进气道的流场分布图谱,在此基础上,对比分析了变形前/后相应状态下进气道流场及其性能参数的变化情况,得到了该类进气道气动变形对其性能的影响规律,结果表明该类进气道在弹性研究范围内若不考虑强度问题则其内通道可不安装支撑,以避免支撑对进气道性能的不利影响及整体结构重量的增加。
A numerical study on influence of the pneumatic deformation on the performance of a single module inlet with thin shell is done in the paper.The deformation curves and the flow contours of the undeformed/deformed inlet under different back pressures,different flight heights,different flight Mach numbers and different wall thicknesses are obtained.The transformation of flow contours and performance parameters of undeformed/deformed inlet is contrastively analyzed based on the former work,and characteristics influence of pneumatic deformation on the performance of the inlet is obtained.In the range of elasticity,the results show that it does not need supports for this kind of inlet in order to decline the total-pressure loss induced by supports and to reduce the mass of the missile.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2011年第1期210-218,共9页
Journal of Astronautics
关键词
航空航天推进系统
薄壳进气道
气动变形
支撑
单模块
气动弹性
Aerospace propulsion system
Inlet with thin shell
Pneumatic deformation
Supports
Single module
Aero-elasticity
