一种异型同心筒发射装置的排导性能仿真研究

Numerical simulation on the drainage performance of a special shaped concentric cylinder launcher

为解决"大弹径、有翼导弹"的发射技术难题,提出了一种"外方内圆"非规则异型同心筒发射装置结构,并采用三维N-S方程、雷诺平均湍流模型和动网格技术对有翼导弹非定常发射过程的燃气排导性能进行数值仿真,获得导弹发射过程中燃气流场流动规律。研究结果表明:内外筒腔和导流锥处燃气流动状态良好,且异型同心筒发射装置的排导效率达到97.8%,可实现燃气的顺利排导,同时,仿真计算得到的压强、温度等流动参数与1∶1状态的地面试验结果保持一致,验证了仿真计算的可靠性。计算结果可为异型结构同心筒发射装置的工程应用可行性提供理论支撑。

In order to solve the technical problem of the large-diameter missile and the winged missile,an irregular concentric launcher structure with square outer cylinder and circular inner cylinder was presented.Moreover,the three-dimensional N-S equation,Reynolds mean turbulence model and dynamic grid technology were used to simulate the gas flow of the winged missile during its unsteady launching process,and the flow pattern could be obtained.The results showed that the gas flow status between the inner and outer cylinders and the guide cone was good.Moreover,the circulation efficiency of the special concentric launcher was 97.8%,so the gas can flow smoothly in the launcher.At the same time,the pressure,temperature and other flow parameters calculated by simulation were consistent with the 1∶1 ground test results,verifying the reliability of the simulation calculation.The calculation results can provide a theoretical support for engineering application feasibility of the special concentric cylinder launchers.