APFSDS外形变化对阻力系数影响分析  

Effect of Aerodynamic Shape Parameters Change on Drag Coefficient of APFSDS

作　　者：岳通 王惠源[1] 张成卿 YUE Tong;WANG Huiyuan;ZHANG Chengqing(School of Mechanical and Electrical Engineering, North University of China, Taiyuan 030051, China)

机构地区：[1]中北大学机电工程学院,太原030051

出　　处：《兵器装备工程学报》2020年第4期41-45,共5页Journal of Ordnance Equipment Engineering

摘　　要：通过改变弹头部长径比,尾翼根梢比,尾翼后缘后掠角的大小,运用计算流体力学对不同外形参数的尾翼稳定脱壳穿甲弹进行气动参数仿真,得到阻力系数及稳定性的变化规律。结果表明:在超音速范围内,尾翼稳定脱壳穿甲弹的稳定性随着马赫数的增加而减小,随着攻角的增加也在减小;其他参数不变时,增大弹头部长径比,有利于降低弹体阻力系数但稳定性也会随着降低;当根梢比及弹头部长径比不变时,增大后缘后掠角,有利于降低弹体阻力系数并提高弹体稳定性;当后缘后掠角及弹头部长径比不变时,增大根梢比,有利于降低弹体阻力系数但弹体稳定性也会降低。The fineness ratio of projectile nose,root-tip ratio of tail and the trailing edge sweepback angle were changed and the aerodynamic parameters at different aerodynamic shape parameters of Armor Piercing Fin Stabilized Discarding Sabot(APFSDS)were simulated by CFD.The variation regularity of drag coefficient and stability with different aerodynamic shape parameters were obtained.The results show that for the supersonic range,stability of fin-stabilized projectile decrease with the increase of mach number and attack angle;Increasing the fineness ratio of projectile nose can reduce the drag coefficient but the stability will also be reduced while keeping up other parameters unchanged.Increasing the trailing edge sweepback angle can reduce the drag coefficient and improve the stability at the same root-tip ratio of tail and fineness ratio of projectile nose;Increasing the root-tip ratio of tail can reduce the drag coefficient but the stability will also be reduced at the same trailing edge sweepback angle and fineness ratio of projectile nose.

关 键 词：尾翼稳定脱壳穿甲弹 计算流体力学 阻力系数 稳定性 攻角 后缘后掠角 

分 类 号：TJ413[兵器科学与技术—火炮、自动武器与弹药工程]