多排斜侧孔膛口制退器流场数值模拟  

Numerical Simulation of Flow Field of Muzzle Brake with Multi-row Oblique-side-holes

作　　者：邱明[1] 谢昊 宋杰[1] 陶宇翔 廖振强[1,2] QIU Ming;XIE Hao;SONG Jie;TAO Yuxiang;LIAO Zhenqiang(School of Mechanical Engineering,Nanjing University of Science and Technology,Nanjing 210094,China;School of Electromechanical Engineering,Suzhou Global Institute,Suzhou 215163,China)

机构地区：[1]南京理工大学机械工程学院,江苏南京210094 [2]苏州高博职业学院机电工程学院,江苏苏州215163

出　　处：《弹道学报》2025年第1期121-128,共8页Journal of Ballistics

基　　金：国家自然科学基金项目(52475108,12072161)。

摘　　要：为精确计算某航炮多排斜侧孔膛口制退器制退效率,综合考虑弹丸对火药气体膨胀的阻碍作用和斜侧孔对气体的加速作用,进行膛口流场数值模拟。首先,对30 mm航炮进行两相流内弹道计算,得到弹丸到达膛口位置时的膛内气流状态;然后,建立膛口流场三维N-S方程,考虑弹丸与火药气体的作用,采用多面体网格静止区域和六面体结构网格运动区域相结合的三维动网格方法,对弹丸经过每排斜侧孔时火药气体三维瞬态流动进行数值模拟,并与不考虑弹丸运动的情况进行对比。结果表明:斜侧孔能导入膛内高压火药气体,并形成超声速气流且从斜后方喷出,从而产生较大的反后坐冲量,制退效率达到38.4%;弹丸对火药气体膨胀存在阻碍作用,在斜侧孔处出现更强的锥形斜激波,从而使更多火药气体从斜侧孔喷出,增加反后坐冲量,因此,此类膛口制退器数值模拟中必须考虑弹丸运动。该研究为新型多排斜侧孔膛口制退器设计、航炮与飞机的动态匹配研究提供了参考。In order to accurately calculate the recoil efficiency of a certain aircraft gun with multi-row oblique-side-holes muzzle-brakes,the numerical simulation on muzzle flow-field was carried out,considering the effect of projectile on propellant gas expansion and the acceleration effect of oblique-side-holes on propellant gas.The correctness of this numerical simulation method was verified by comparing the numerical simulation results of the muzzle flow field of a 12.7mm weapon with experimental results.The two-phase-flow internal-ballistic model of 30 mm aircraft gun was calculated numerically,and the flow state in the bore while the projectile reaching the bore position was obtained under the initial condition.The three-dimensional N-S equations of the muzzle flow-field were established,taking into account the interaction between the projectile and the propellant gas.A three-dimensional moving-grid method combining a polyhedral mesh for the stationary region and a hexahedral structured mesh for the moving region was adopted to numerically simulate the three-dimensional transient flow of the propellant gas when the projectile passes through each row of oblique-side-holes,which was compared with the case without considering the projectile motion.The results show that the oblique-side-holes can introduce high-pressure propellant gas into the barrel and generate supersonic airflow from the oblique rear,thereby producing a large recoil impulse.The recoil efficiency reaches 38.4%.The projectile impedes the expansion of propellant gas,resulting in stronger conical oblique shock waves at the oblique-side-holes.As a result,more propellant gas is ejected from the oblique-side-holes,increasing the recoil impulse.Therefore,projectile motion must be considered in numerical simulations of this type of muzzle brake.This research provides reference for the design of new multi-row oblique-side-holes muzzle-brakes and the dynamic matching between cannons and aircraft.

关 键 词：航炮 制退器 斜侧孔 动网格 三维流场 制退效率 

分 类 号：TJ385[兵器科学与技术—火炮、自动武器与弹药工程]