一种新型灵巧枪弹的气动特性研究
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摘要
相对普通枪弹,灵巧枪弹具有小尺寸和高命中精度的特点,可显著增强单兵战斗力和生存能力。考虑器件尺寸和气动特性的技术要求,设计了一种新型增程灵巧枪弹的气动外形。该灵巧枪弹与普通枪弹在外形尺寸上有很大区别,气动特性及流场特征尚不明了,因此有必要对灵巧枪弹气动特性进行深入研究。采用数值仿真和风洞实验的方法研究了灵巧枪弹的气动特性,并分析了弹尾外形尺寸变化对灵巧枪弹气动特性的影响规律。研究结果表明:数值仿真结果和风洞实验结果基本一致,证明了数值仿真方法的可行性;随着灵巧枪弹收缩段长度的增加,阻力先减小、后增大,升力和俯仰力矩绝对值先基本保持不变、后增大;随着交界半径的增大,阻力、升力和俯仰力矩绝对值均减小;随着弹底半径的增大,阻力先增大、后减小,升力和俯仰力矩绝对值先减小、后增大。
The smart bullet is expected to remarkably enhance the combat effectiveness and survivability of individual soldiers due to its miniature size and high hit accuracy. Considering the technical requirements of device sizes and aerodynamic characteristics,an aerodynamic shape of a novel smart bullet is designed. The overall dimensions of the smart bullet are quite different from those of the normal bullet,and its aerodynamic and flow field characteristics are still unknown. Therefore,it is necessary to study the aerodynamic characteristics of the smart bullet. The aerodynamic characteristics of smart bullet are studied through numerical simulation and wind tunnel experiments,and the influence of dimensional change of bullet tail on the aerodynamic characteristics of smart bullet is analyzed. The research results show that the numerically simulated results are basically consistent with the wind tunnel experimental results,which proves the feasibility of the numerical simulation method. With the increase in the length of contraction section,the drag decreases first and then increases,while the lift and the absolute value of pitching moment remain unchanged first and then increase. With the growth of the radius of intersection,the absolute values of drag,lift and pitching moment decrease. With the increase in the radius of bottom,the drag increases first and then decreases,while the absolute values of lift and pitching moment decrease first and then increase.
The smart bullet is expected to remarkably enhance the combat effectiveness and survivability of individual soldiers due to its miniature size and high hit accuracy. Considering the technical requirements of device sizes and aerodynamic characteristics,an aerodynamic shape of a novel smart bullet is designed. The overall dimensions of the smart bullet are quite different from those of the normal bullet,and its aerodynamic and flow field characteristics are still unknown. Therefore,it is necessary to study the aerodynamic characteristics of the smart bullet. The aerodynamic characteristics of smart bullet are studied through numerical simulation and wind tunnel experiments,and the influence of dimensional change of bullet tail on the aerodynamic characteristics of smart bullet is analyzed. The research results show that the numerically simulated results are basically consistent with the wind tunnel experimental results,which proves the feasibility of the numerical simulation method. With the increase in the length of contraction section,the drag decreases first and then increases,while the lift and the absolute value of pitching moment remain unchanged first and then increase. With the growth of the radius of intersection,the absolute values of drag,lift and pitching moment decrease. With the increase in the radius of bottom,the drag increases first and then decreases,while the absolute values of lift and pitching moment decrease first and then increase.
引文
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[2]SAHU J.CFD simulations of a finned projectile with microflaps for flow control[J].International Journal of Aerospace Engineering,2017,2017(5):1-15.
[3]LAWHORN W S,CLINKENBEARD I L.Small caliber guided projectile:US4537371A[P].1985-08-27.
[4]BARRETT R.Invention and evaluation of the barrel-launched adaptive munition(BLAM)[R].Eglin AFB,FL,US:Wright Laboratory,1995.
[5]BARRETT J,ROLIN F.Guided bullet:US 5788178[P].1998-08-04.
[6]JONES J F,KAST B A,KNISKERN M W,et al.Small caliber guided projectile:US7781709 B1[P].2010-08-24.
[7]DYKES J,COSTELLO M,FRESCONI F.Periodic projectile linear theory for aerodynamically asymmetric projectiles[J].Proceedings of the Institution of Mechanical Engineers,Part G:Journal of Aerospace Engineering,2014,228(11):2094-2107.
[8]STRUB G,DOBRE S,GASSMANN V.Pitch-axis identification for a guided projectile using a wind-tunnel-based experimental setup[J].IEEE/ASME Transactions on Mechatronics,2016,21(3):1357-1365.
[9]赵俊波,梁彬,付增良,等.机动式再入弹头小滚转气动力风洞试验技术[J].空气动力学报,2016,34(1):53-58.ZHAO J B,LIANG B,FU Z L,et al.Experimental technique for micro rolling aerodynamics of a maneuvering reentry body[J].Acta Aerodynamica Sinica,2016,34(1):53-58.(in Chinese)
[10]SILTON S,HOWELL B.Aerodynamic and flight dynamic characteristics of 5.56-mm ammunition:M855[R].Adelphi,MD,US:Army Research Laboratory,2010.
[11]FRESCONI F,CELMINS I,HOWELL B.Obtaining the aerodynamic and flight dynamic characteristics of an asymmetric projectile through experimental spark range firings[C]∥Proceedings of AIAA Atmospheric Flight Mechanics Conference.Boston,MA,US:AIAA,2013.
[12]雷娟棉,李田田,黄灿.高速旋转弹丸马格努斯效应数值研究[J].兵工学报,2013,34(6):718-725.LEI J M,LI T T,HUANG C.A numerical investigation of Magnus effect for high-speed spinning projectile[J].Acta Armamentarii,2013,34(6):718-725.(in Chinese)
[13]雷娟棉,张嘉炜,谭朝明.小攻角下船尾外形对旋转弹丸马格努斯效应影响的数值研究[J].兵工学报,2017,38(9):1705-1715.LEI J M,ZHANG J W,TAN Z M.Influence of boattail on the Magnus effect of spinning non-finned projectile at small angles of attack[J].Acta Armamentarii,2017,38(9):1705-1715.(in Chinese)
[14]SAILARANTA T,HONKANEN T,LAAKSONEN A.Bullet turning at trajectory apex[J].Journal of Aerospace Engineering,2014,27(5):04014030.
[15]吴志林,袁钰.尾翼式修正枪弹气动力计算研究[J].弹箭与制导学报,2014,34(2):127-130.WU Z L,YUAN Y.The study on aerodynamics evaluation of winged guided bullet[J].Journal of Projectiles,Rockets,Missiles and Guidance,2014,34(2):127-130.(in Chinese)
[16]高炳龙.基于Fluent的可控枪弹弹丸气动力参数计算仿真[D].太原:中北大学,2014.GAO B L.Analysis and simulation of aerodynamic parameter of controllable bullet on Fluent[D].Taiyuan:North University of China,2014.(in Chinese)
[17]孟鹏,陈红彬,钱林方,等.弹带对高速旋转弹丸气动特性影响的数值模拟[J].兵工学报,2017,38(12):2363-2372.MENG P,CHEN H B,QIAN L F,et al.Numerical investigation on the effect of rotating band on aerodynamic characteristics of high-speed spinning projectile[J].Acta Armamentarii,2017,38(12):2363-2372.(in Chinese)
[18]SAHU J,HEAVEY K.Parallel CFD computations of projectile aerodynamics with a flow control mechanism[J].Computers&Fluids,2013,88:678-687.
[19]CAI H M.Virtual flight simulation of a dual rotor micro air vehicle[J].International Journal of Computational Fluid Dynamics,2015,29(2):192-198.
[20]MENTER F R.Zonal two equation k-ωturbulence models for aerodynamic flows[C]∥Proceedings of the 23rd Fluid Dynamics,Plasma dynamics,and Lasers Conference.Orlando,FL,US:AIAA,1993.