通过数值模拟对可偏转头部弹在0.35Ma、偏转角为0°~5°时的气动特性进行相关研究。当头部发生偏转时,压心发生变化且产生横向作用力使得弹丸偏离原弹道。随着偏角的增加,压心先向着头部移动;当偏角进一步增大时,压心不再继续向前移动。攻角的存在使得阻力系数增大,而Z向力系数基本不变。

Based on aerodynamic characteristics of missiles with a deflected angle of forehead at the Mach 0.35 and deflection angle from 0 degree to 5 degrees by numerical simulation. Through the study, it is found that the deflection of head leads to the change of the pressure center and the generation of lateral forces which make the projectile deviate from the original trajectory. As the dec lination increases, the pressure center first moves toward the head, when the angle further increases, the pressure center stops to move forward. The existence of amakes the drag coefficient increases, while the Z-force coefficient has no change basically.