新型优化同心筒自力发射流场机理与降温效果

Research on Flow Field Mechanism and Cooling Effect of a New Optimized Concentric Canister Launcher

针对同心筒自力发射结构优化与热环境改善的问题,基于雷诺平均方程及轴对称N-S方程,依托弹性变形和网格再生成方法结合的动网格技术,对3种不同结构形式同心筒发射装置的二维轴对称流场进行了非定常数值计算,得到了不同结构条件下动态的流场机理及导弹热环境特性。计算结果显示:导流器方案能实现燃气流迅速顺利排导;筒底收缩段设计能有效遮挡反溅燃气流;筒口导流板结构较好抑制了内筒的"倒吸效应",确保导弹和内筒的热安全;揭示了优化同心筒的流场结构与降温机理,可为相关研究提供参考。

Based on the RANS governing equations,axisymmetric N-S equation and dynamic mesh technology with spring based smoothing method and remeshing method,the axisymmetric flow fields of different shapes of concentric canister launcher have been simulated numerically,both the flow field mechanism and missile thermal environment characteristics of different structure form are obtained to deal with the structural optimization and thermal environment improving problem of concentric canister launcher. The numerical results show that the deflector scheme is in favor of exhausting the jet quickly and smoothly; through the design of the shrinking part at the rump of internal cylinder,the reflection of the high temperature jet can be reduced significantly; the reverse absorption effect of jet flow can be well inhibited,so the thermal safety of missile and internal cylinder can be guaranteed. Moreover,the flow structure and cooling mechanism of the concentric canister launcher scheme are revealed,and the numerical results can provide important guidance for relative investigations.