枪弹外形对阻力特性影响的数值模拟
|
摘要
运用数值模拟方法计算了不同外形尺寸对某7.62 mm枪弹阻力特性的影响规律。分别计算枪弹在不同头部、尾部尺寸及带刻痕时阻力系数随马赫数的变化,并与标准枪弹外形尺寸下的阻力系数变化规律进行比较。计算表明:头部圆弧直径越大即头部越锐长,阻力系数越小;在一定范围内,尾部锥角越大,阻力系数越小;头部圆弧部的影响大于尾部截锥体的影响。带刻痕时枪弹阻力系数大于标准弹的阻力系数。
The method of numerical simulation was used to calculate influence of bullet size on drag coefficient of one 7. 62 mm bullet. Different head or tail size was calculated and the influence of nick was also considered in the simulation. From the comparison between the drag coefficient data changing with different much numbers in simulation and that calculated under standard bullet size,it is found that the larger the size of head or tail is,the smaller the drag coefficient is and the influence of the head size is larger than the tail size. The coefficient of the bullet with nick is larger than that with standard size.
The method of numerical simulation was used to calculate influence of bullet size on drag coefficient of one 7. 62 mm bullet. Different head or tail size was calculated and the influence of nick was also considered in the simulation. From the comparison between the drag coefficient data changing with different much numbers in simulation and that calculated under standard bullet size,it is found that the larger the size of head or tail is,the smaller the drag coefficient is and the influence of the head size is larger than the tail size. The coefficient of the bullet with nick is larger than that with standard size.
引文
[1]浦发,芮筱亭.外弹道学[M].北京:国防工业出版社,1989.
[2]Sadowski L M,Malatesta E T,Huerta J.30mm tubular projectile,ADB 087370[R].US:Army Armament Research and Development Center Dover NJ Fire Control and Small Caliber Weapon Systems Lab,1984.
[3]武晓松,王栋,郭锡福.弹丸超声速绕流的NavierStokes模拟[J].空气动力学报,1998,16(2):162-166.
[4]Lewis M J.A hypersonic propulsion airframe integration overview,AIAA Paper 2003-4405[R].2003.
[5]崔凯,杨国伟.基于CFD分析的弧形翼导弹气动外形优化[J].中国科学,2009,39(6):865-873.
[6]许安勇.二维弹道修正弹的气动特性研究[D].南京:南京理工大学,2010.
[7]王鹏飞,曹红松,解宁波,等.高旋火箭弹增程稳定性设计及启动特性分析[J].弹箭与制导学报,2012,32(5):124-126.
[8]李艳玲.低阻空心弹的数值设计研究[D].南京:南京理工大学,2012.
[9]胡志鹏,刘荣忠,郭锐,等.基于弹丸图像的末敏弹阻力系数计算方法[J].探测与控制学报,2012,34(3):8-18.
[10]黄振贵,李艳玲,陈志华,等.空心弹的阻力特性与气动外形数值分析[J].兵工学报,2013,34(5):535-540.
[11]雷文星.BM-21火箭弹改型气动力特性分析[D].太原:中北大学,2013.
[12]吴子牛.计算流体力学基本原理[M].北京:科学出版社,2001.
[13]陆家鹏,谭兴良,雷志义,等.自动武器气体动力学[M].北京:兵器工业出版社,1991.
[14]Paul Weinacht.Virtual wind tunnel method for projectile aerodynamic characterization[R].US:US Army Research Laboratory,Aberdeen Proving Ground,2007.
[2]Sadowski L M,Malatesta E T,Huerta J.30mm tubular projectile,ADB 087370[R].US:Army Armament Research and Development Center Dover NJ Fire Control and Small Caliber Weapon Systems Lab,1984.
[3]武晓松,王栋,郭锡福.弹丸超声速绕流的NavierStokes模拟[J].空气动力学报,1998,16(2):162-166.
[4]Lewis M J.A hypersonic propulsion airframe integration overview,AIAA Paper 2003-4405[R].2003.
[5]崔凯,杨国伟.基于CFD分析的弧形翼导弹气动外形优化[J].中国科学,2009,39(6):865-873.
[6]许安勇.二维弹道修正弹的气动特性研究[D].南京:南京理工大学,2010.
[7]王鹏飞,曹红松,解宁波,等.高旋火箭弹增程稳定性设计及启动特性分析[J].弹箭与制导学报,2012,32(5):124-126.
[8]李艳玲.低阻空心弹的数值设计研究[D].南京:南京理工大学,2012.
[9]胡志鹏,刘荣忠,郭锐,等.基于弹丸图像的末敏弹阻力系数计算方法[J].探测与控制学报,2012,34(3):8-18.
[10]黄振贵,李艳玲,陈志华,等.空心弹的阻力特性与气动外形数值分析[J].兵工学报,2013,34(5):535-540.
[11]雷文星.BM-21火箭弹改型气动力特性分析[D].太原:中北大学,2013.
[12]吴子牛.计算流体力学基本原理[M].北京:科学出版社,2001.
[13]陆家鹏,谭兴良,雷志义,等.自动武器气体动力学[M].北京:兵器工业出版社,1991.
[14]Paul Weinacht.Virtual wind tunnel method for projectile aerodynamic characterization[R].US:US Army Research Laboratory,Aberdeen Proving Ground,2007.