针对导弹从内埋武器舱发射后受到复杂气动干扰对初始弹道和自控终点散布产生影响的问题,研究了计算流体力学(CFD)与六自由度方程联合数值仿真方法,建立了载机和导弹的计算模型,编写了弹道程序,基于动网格技术,准确模拟了导弹的运动过程,获得了在发射初始无控段导弹的受力、位移和姿态角等参数,并为有控弹道自控终点散布仿真提供初始条件。仿真结果表明,气动干扰对内埋导弹发射后初始弹道和自控终点纵向、侧向散布影响明显。该研究可解决导弹气动与运动紧密耦合的问题。

In order to solve the problem that complex aerodynamic interferences which exist in missile separating from cavity effects missile' s initial trajectory and auto-control terminal point scatter. Computational fluid dynamic (CFD) method coupled with 6 degree-of-freedom equations was established. Aircraft with missile computational model and trajectory program was developed. The missile motion was captured accurately through the dynamic mesh technology. Parameters such as force, displacement and attitude were got and passed as inputs of missile auto-control trajectory program and the scatter of auto-control terminal point was computed. The simulation results indicated the great influence on the initial trajectory parameters and on the longitudinal and lateral scatter of auto-control terminal point. The method can deal with pneumatic tight coupled with kinematic problems of missile.