无伞末敏弹弹性尾翼气动特性研究  

Research on aerodynamic characteristics of elastic 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,江苏南京210094

出　　处：《南京理工大学学报》2015年第2期133-138,共6页Journal of Nanjing University of Science and Technology

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

摘　　要：针对无伞末敏弹尾翼薄、下落过程中容易发生变形甚至振动的问题,该文采用ANSYS Workbench对其弹性尾翼进行了双向流固耦合分析。结果表明,尾翼挠度随来流速度的增加呈准线性增加,最大挠度出现在向迎风面弯折的较大翼外侧角点,随来流速度的增加速率约为0.05 mm/(m·s-1)。随攻角的增加,阻力系数呈约0.05/(°)的准线性递减而升力系数呈约0.08/(°)的准线性递增。尾翼的高压区出现在平面部分与向迎风面弯折尾翼的连接处,且随着来流速度的增加,高压区作用面积逐渐扩大。In view of that the wings of non-parachute terminal sensitive projectile （TSP） may deform or vibrate during the falling process due to their thin thickness, the ANSYS Workbench, a two-way fluid-structure interaction method is used to analyze the elastic wings by the two-way fluid-structure interaction. The results show that the wing deflection increase when the velocity increases. The largest deflection lies in the outer corner point of the bigger wing bending towards the windward when the in- creasing ratio is about 0.05 mm/（ m s-1 ）. The drag coefficient decreases by 0.05/（°） and the lift coefficient increases by 0.08/（°） with the attack angle increasing. The high-pressure area lies in the connection region of the plate wing and the wing bending towards the windward. The impact area is expanded with the increase of the incoming velocity.

关 键 词：无伞末敏弹 弹性尾翼 气动特性 流固耦合 

分 类 号：TJ414.5[兵器科学与技术—火炮、自动武器与弹药工程]