弹体尾部斜锥面形状对侵彻偏转的影响

Influence of Penetration Deflection by the Shape of Tail Oblique Cone of Projectile

针对弹体斜侵彻多层靶时弹道发生的偏转问题,建立了弹体尾部为斜锥面结构的弹体侵彻偏转理论计算模型,获得了当速度为0.2~1.2km/s、着角为-30°~20°、弹体半径为30~60 mm、尾飘斜面与弹轴的夹角为0°~4°时偏转随尾部结构的变化规律,通过与试验结果进行对比,验证了模型的准确性。结果表明:弹体侵彻仰靶时,弹尾形成负的偏转力矩,弹体产生“低头”效果;弹体侵彻俯靶时,弹尾形成正的偏转力矩,弹体产生“抬头”效果;弹体尾部斜锥面产生的垂直弹轴的偏转力矩约为平行弹轴的偏转力矩的100倍;增大尾飘斜面与弹轴的夹角、尾飘长度、弹体半径均可增大偏转力矩;与增大尾飘长度相比,增大尾飘斜面与弹轴的夹角对增大偏转力矩更有效。

Aiming at the problem of deflection when the projectile obliquely penetrates a multi-layer target,a theoretical calculation model of the projectile deflection caused by the oblique cone structure of the projectile tail is established,and the change rule of the deflection with the tail structure is obtained at the working conditions of the velocity of 0.2−1.2 km/s,the angle of attraction of−30°−20°,the radius of the projectile body of 30–60 mm,and the angle between bevel plane of tail and the projectile shaft of 0°−4°.Moreover,the accuracy of the model is verified by comparing with the test results.The results showed that the tail of the projectile forms a negative deflection moment and the projectile produces a“head down”effect when the tail of the projectile penetrated upward target,and the tail of the projectile forms a positive deflection moment and the projectile produces a“head up”effect when the tail of the projectile penetrated downward target;the deflection moment of vertical axis is about 100 times greater than that of parallel axis.The deflecting moment can be increased by increasing the angle between bevel plane of tail and the projectile shaft,the length of the tail,and the radius of the projectile.Increasing the angle between bevel plane of tail and the projectile shaft is more effective in increasing the deflection moment than increasing the tail length.