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为分析在时序抛撒方式下子母弹多体干扰流场特性及其对各舱段弹体气动特性的影响,基于流体控制方程与六自由度刚体运动方程,结合非结构动网格技术,分别对两种时序抛撒方式及后舱子弹单独抛撒方式下的子母弹三维非定常分离流场进行数值模拟,得到不同抛撒时序下的分离流场特性及其气动干扰特性,揭示各舱段子弹在不同分离阶段的气动干扰相互作用过程。研究结果表明:在时序抛撒分离过程中各弹体间激波不断地交错干扰,增加了流场结构的复杂性;前舱子弹的激波干扰使得后舱段子弹气动分离参数较低,分离效率较慢,尤其在短时序间隔下,后舱弹体受前舱子弹干扰较为严重,弹体的安全分离受到影响。
In order to analyze the multi-body disturbance flow field and the effect on the aerodynamic characteristics of the projectiles in the time series mode, based on the fluid control equation and the six-degree-of-freedom rigid body equation of motion combined with the unstructured moving grid technique, And the three-dimensional unsteady separation flow field of submunition in the rear-hatch bullet alone was numerically simulated to obtain the characteristics of the flow field and the aerodynamic interference under different scattering timings. It was revealed that the bullet at each separation stage Pneumatic interference interaction process. The results show that the shocks between the projectiles intermingle intermittently and increase the complexity of the flow field structure in the process of timing discharge. The shock wave of the anterior projectile causes the aerodynamic separation parameters of the projectile after the projectile to be lower, and the separation efficiency Slower, especially at short time intervals, the rear fuselage is more severely interfered by the frontal bullets and the safe separation of the projectiles is affected.