某型反坦克导弹气动仿真方法研究

Research on Simulation Method of Aerodynamics for a Certain Anti-tank Missile

为了获取某型反坦克导弹的气动参数,基于开源的OpenFOAM软件包,针对某型反坦克导弹的外形,在对导弹底部结构以及弹翼和尾舵外形进行处理后,运用结构化网格划分方法和局部加密方法建立了气动仿真模型。采用带可压缩修正的湍流模型,进行了气动仿真计算,并将计算结果与风洞试验数据进行了对比,结果表明:仿真计算所得气动参数与风洞试验结果符合较好,误差较小,证明了此仿真方法具有较好的可信度。此种方法可以推广运用于类似外形导弹的气动仿真中,能够起到减小耗费、提高效率和缩短研制周期的作用。

In order to obtain aerodynamic parameters of a certain anti-tank missile,based on OpenFOAM software which is of open source,in view of contour of the anti-tank missile,after processing the missile bottom structure and configuration of wings as well as trail rudder,using structured grid partition method and local refinement method,the simulation model of aerodynamics is established. The simulation calculation of aerodynamics proceeds with turbulence model with compressibility and the results is compared with the wind tunnel test data. It is shown that the simulation parameters of aerodynamics are close to the wind tunnel test data and the error is little,and a better reliability of the simulation method is proved.The method can be generalized for aerodynamics simulation of missile with close shape,which can reduce the cost,improve the efficiency and shorten the development cycle.