双翼无伞末敏弹阻力系数试验及仿真  

Experiments and Simulation of Drag Coefficient of TPS

作　　者：吕胜涛[1] 郭锐[1] 刘荣忠[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,南京210094

出　　处：《弹箭与制导学报》2015年第5期45-48,共4页Journal of Projectiles,Rockets,Missiles and Guidance

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：为分析无伞末敏弹稳定翼片对弹体阻力系数的影响,设计了高塔试验对不同尾翼结构参数末敏弹进行研究。文中设计一种"S"型尾翼作为无伞末敏弹的减速装置,进行了不同翼片结构尺寸末敏弹的自由飞行试验,得到不同尾翼组合末敏弹的阻力系数,分析了尾翼结构参数对阻力系数的影响。并对试验用弹进行数值仿真分析,结果发现,试验值与仿真值吻合良好。Free flight experiments were carried out to study how wing＇s structure parameters affect drag coefficient of terminal sensitive projectile（ TSP）. One S-shaped wing was designed to decelerate TSP. Drag coefficients of TSP with different wings were calculated by free flight experiments. Numerical simulations were done by means of commercial CFD Solver Fluent. It turns out that the experiment results fit the simulation results quite well.

关 键 词：无伞末敏弹 阻力系数 自由飞行试验 尾翼结构 数值仿真 

分 类 号：TJ414.5[兵器科学与技术—火炮、自动武器与弹药工程]