无伞末敏弹稳定翼片流固耦合特性研究  

Research on the Fluid-structure Interaction of C-wing of Non-parachute Terminal Sensitive Projectile

作　　者：吕胜涛[1] 马晓冬[1] 刘荣忠[1] 郭锐[1] 

机构地区：[1]南京理工大学机械工程学院,南京210094

出　　处：《科学技术与工程》2014年第6期150-153,共4页Science Technology and Engineering

基　　金：国家自然科学基金(11372136);国家自然科学基金-青年科学项目(1102088);高等学校博士学科点专项科研基金-新教师类(200932192006)资助

摘　　要：以某结构双翼无伞末敏弹C型尾翼为研究对象,通过对其进行流固耦合计算,得到此类型尾翼的气动特性。结果表明,尾翼平面部分在气动力作用下仍保持平面形状,两弯折面发生弯曲。刚、弹性尾翼阻力系数及二者的偏差随攻角的增大而减小,在30°攻角时两种尾翼的阻力系数几乎相等。迎风面最大压力随来流速度的增加呈现递增趋势,相同来流速度时,大攻角下的最大压力大于小攻角下的最大压力。尾翼对称面背风面出现两个大小大致相等的涡,呈现蝴蝶状低压区。C-wing of the double-wing non-parachute terminal sensitive projectile is simulated and got its aerodynamic characteristic.The results show that drag coefficient of both rigid wing and elastic wing decrease as attack angle grows and they equal at 30° attack angle.The max pressure of windward increases as flow rate grows,and the max pressure at a larger attack angle is higher than that at a smaller attack angle under same flow rate.Two whirlpools at same size appear at the leeward side of wing＇s symmetrical plane while a butterfly-shaped area of low pressure presents as well.

关 键 词：流固耦合 气动弹性 阻力系数 压力分布 

分 类 号：TJ414.5[兵器科学与技术—火炮、自动武器与弹药工程]