无伞末敏弹尾翼动态性能仿真分析  

Simulation of Aerodynamic Characteristics on Wing of Non-Parachute Terminal Sensitive Projectile

作　　者：吕胜涛[1] 刘荣忠[1] 郭锐[1] 马晓冬[1] 

机构地区：[1]南京理工大学智能弹药技术国防重点学科实验室,江苏南京210094

出　　处：《计算机仿真》2015年第9期10-13,71,共5页Computer Simulation

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)

摘　　要：尾翼作为为无伞末敏弹弹体提供大部分阻力及转动力矩的组成部分,气动特性问题成为末敏弹设计及优化工作的重心。尾翼厚度较小,在末敏弹运动过程中会受气动力作用而发生弹性变形,而无伞末敏弹复杂的外形结构及大攻角的运动状态难以采用常规方法进行气动力测量。为准确分析动态性能,根据功的互等理论,建立了无伞末敏弹平板尾翼的挠曲方程,并计算得到了尾翼在均布气动载荷作用下弯曲变形的解析解;采用双向流固耦合方法,获得了尾翼挠曲变形仿真解。结果显示,平板尾翼短边挠度曲线呈准线性,靠近约束边角点挠度最小。约束边挠度曲线不规则,角点处挠度最大。非约束长边挠度曲线较为平缓,两角点处挠度最小,与理论结果相吻合。The aerodynamic characteristics of wings of non-parachute terminal sensitive projectile （TSP） have been focused on because wings provide most drag and moment for TSP. The wings would deflect during the falling process of non-parachute TSP because of wings＇ small thickness. And the aerodynamic parameters of TSP can hardly be measured for its complex structures and movement status at large attack angle. Based on the reciprocal theorem, this paper analyzed the flexural characteristics of the plate wing and gets certain equation of the plane of flexure. A two-way fluid-structure interaction （FSI） method was used to analyze the wing＇s deflection based on ANSYS Work- bench. The results show that the quasi-linear deflection curve of short border appears, and while the corner spot which is close to the restrained border deflects the least. The restrained border deflects unregularly while the corner spot deflects the largest. The deflection curve of long border which is not restrained changes steadily while two corner spots deflect the least.

关 键 词：平板尾翼 无伞末敏弹 互等理论 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]