导弹热发射方式增推效能研究

为研究导弹热发射增推效能,设计了3种不同方式的排导空间。建立导弹热发射过程的控制方程和导弹全区域结构化网格模型,使用计算流体力学方法进行仿真,分别采用2阶迎风格式和全隐式方法进行空间离散和时间离散;计算了3种不同排导空间条件下导弹的出筒过程、出筒速度,分析导弹发射时筒内气动特征和导弹在发射筒内运动时增推力随导弹位移的变化过程。数值计算结果与原理验证试验结果符合较好。对不同条件下导弹出筒速度的仿真计算结果表明,采用筒式热发射,可以通过改变排导空间的方法实现燃气能量的再利用,将筒内燃气的气动力转换为推动导弹运动的推力,形成额外的增推力,提升导弹筒内运动速度,降低导弹出筒消耗的能量。

Research on Efficiency of Additional Thrust of Thermal Launching

In order to study the increased thrust of thermal launching missile, three different exhaust spaces are designed, and the governing equations for simulating the thermal launch process of missile and a region-wide structured grid model of missile are established using CFD method. Second-order upwind scheme and fully implicit method are used for spatial discrete and time discrete, respectively. The process and velocity of missile exiting from launch tube in three different exhaust spaces are calculated. The aerodynamic characteristics of missile and the changing process of increased thrust for the motion of missile in launcher are analyzed. The numerical results are consistent with the experimental results. The results show that the exhaust space can be changed to achieve the re-use of gas energy, and convert the aerodynamic force to a thrust for missile motion in order to improve the velocity of missile and reduce the energy consumption of missile launching.