子弹对弹舱内压力分布特性影响实验研究  

Influence of submuniton to the cabin's pressure distribution wind tunnel investigation

作　　者：雷娟棉 吴甲生[1] 

机构地区：[1]北京理工大学宇航学院,北京100081

出　　处：《空气动力学学报》2012年第3期328-333,共6页Acta Aerodynamica Sinica

基　　金：预研基金

摘　　要：介绍了所设计的子弹-母弹气动干扰风洞实验研究方案的特点及实验装置,利用该装置进行了子弹对弹舱内压力分布影响的实验。实验结果表明:单独母弹弹舱内压力分布符合过渡式空腔流动规律,即在前端面后的区域为流动分离所形成的低压区(Cp<0),经Cp=0点过渡到Cp>0的区域;后端面对弹舱内流动起阻滞作用,在后端面左右拐角处存在流动缓慢的"死水区";母弹攻角对弹舱内的流动影响显著,正攻角起压缩作用,使前端面后的流动分离区内Cp>0降低,使分离区的纵向范围缩小,使Cp>0区域内的Cp值增大,负攻角起膨胀作用;子弹对母弹弹舱内的流动起压缩作用,当子弹为正攻角时,子弹对弹舱内流动的压缩作用降低。A self-designed submunition-dispenser aerodynamic interference wind tunnel experiment device and the experiment program's feature are introduced.With the device the pressure distribution influence experiment of submunition to its cabin is conducted.The experiment results show that the cabin's pressure distribution represents the transitional-type cavity flow while there isn't submuntion,that is to say the region after the front-face of the cabin is a low pressure(Cp<0) area which caused by the flow separation,and translate to the region through the point Cp=0.The back-face blocks the flow in the cabin,so there is the slowly flow field namely 'dead zone' at the corner front back-face.The dispenser's angles of attack have an observably effect upon the flow field in the cabin,the positive angle of attack compress the flow,which make the pressure coefficient |Cp| of the flow separation area after the front-face decreased and the longitudinal flow separation region shrank;and that the positive angle of attack of the dispenser also makes the cabin's Cp value of the Cp>0 region increases.The dispenser's negative angle of attack makes the cabin's flow expanded.The effect of submunition to the cabin's flow is compressible but while the submunition is positive angle of attack relative to the dispenser,the compressive effect reduced.

关 键 词：子母弹 空腔流动 压力分布 气动干扰 风洞实验 

分 类 号：V211.24[航空宇航科学与技术—航空宇航推进理论与工程]