内埋式航空兵器投放过程的CFD/RBD数值仿真研究

CFD/RBD Numerical Simulation Research on the Process of Buried Aviation Weapon Launch

飞翼布局因其特殊的构型,表现出与常规飞行器较大的性能差异。内埋式弹舱能够帮助战机提高其隐身性能,但舱门干扰和空腔结构下流动较为复杂,多枚弹体在分离过程中极有可能互相发生碰撞或与武器舱接触,威胁载机安全,因而提高内埋式武器的分离品质至关重要。使用改进的非结构嵌套网格径向基函数插值方法、耦合流动控制方程和刚体动力学方程(RBD,Rigid Body Dynamics),对一类常规“W”型飞翼布局内埋式武器的分离过程进行数值模拟,分离过程考虑了分离间隔(0 s/0.01 s/0.03 s)对弹体分离品质的影响。仿真结果表明,在前后舱2枚弹体分离的过程中,采用时序分离的方式能够有效提高后舱分离弹体的分离品质,整个分离过程中弹体的姿态变化较为平稳。

Because of its special configuration,the flying wing layout aircraft shows a big difference in performance from conventional aircraft.Embedded weapon cabin can help fighters improve stealth performance,but the door interference and the flow under the cavity structure are more complicated.Multiple missiles are very likely to collide with each other or contact the weapon cabin during the separation process,affecting the safety performance of the carrier aircraft,so improving the separation quality of embedded weapons is very important.Using an improved non-structural overset grid radial basis function interpolation method,coupling flow control equations and rigid body dynamics equations,the separation process of a conventional“W”type flying wing layout embedded weapons is numerically simulated.In the separation process,the effect of separation interval(0 s/0.01 s/0.03 s)on the separation quality of the projectile is fully considered.The simulation results show that during the separation of the front and rear cabin,the timing separation method can effectively improve the separation quality of the rear cabin separation projectile,and the attitude of the projectile changes smoothly during the entire separation process.