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首页> 外文期刊>Proceedings of the Institution of Mechanical Engineers >Simulation of gas flow and additional thrust with missile launching from concentric canister launcher
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Simulation of gas flow and additional thrust with missile launching from concentric canister launcher

机译：从同心筒发射器发射导弹来模拟气流和附加推力

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摘要

A computational fluid dynamics method has been applied to simulate the exhaust gas flow and the additional thrust during a missile launching from concentric canister launcher. The unsteady, axisymmetric Reynolds-averaged Navier-Stokes equations with renormalization group k - ε turbulence model are numerically solved here. The dynamic mesh method is utilized to simulate the movement of the missile. Computational fluid dynamics results show that the additional thrust is an important thrust and fluctuates with the movement of the missile for launching from concentric canister launcher. The mechanism for producing and influencing the additional thrust is typically relevant to the choking states of exhaust gases at the inlet and outlet of the annular tube of concentric canister launcher, responding to the jet impinging on the bottom of the launcher, the approximate wall jet, and the friction effect in the tube.
机译：一种计算流体动力学方法已被应用于模拟导弹从同心筒发射器发射期间的废气流和附加推力。在此数值求解具有重归一化组k-ε湍流模型的非稳态轴对称Reynolds平均Navier-Stokes方程。动态网格法被用来模拟导弹的运动。计算流体动力学结果表明，附加推力是一个重要推力，并随着导弹从同心筒发射器的发射运动而波动。产生和影响附加推力的机制通常与同心筒发射器的环形管的入口和出口处的废气的states流状态有关，这是响应撞击在发射器底部的射流，近似壁射流，以及管内的摩擦效果。

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