气动变形对独立模块薄壳进气道性能影响研究  

Study on Influence of Pneumatic Deformation on the Performance of a Single Module Inlet with Thin Shell

作　　者：靖建朋[1,2] 郭荣伟[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016 [2]中国人民解放军驻西飞公司军事代表室,西安710089

出　　处：《宇航学报》2011年第1期210-218,共9页Journal of Astronautics

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.

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 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]