导弹发射筒盖开启过程数值计算及试验

Numerical Calculation & Experiments for the Opening Process of Missile Launcher's Cover

为了研究导弹发射时燃气产生的压力开启前后易碎盖的方式,利用计算流体技术和试验方法对某型导弹发射时开盖技术进行了数值模拟和试验,建立了导弹和发射筒的二维和三维计算模型,研究结果表明,某型导弹采用易碎前后盖技术,后易碎盖由发动机燃气直接冲破,前易碎盖靠发射时产生的扰动波打开,通过合理配置发射筒前后易碎盖开盖条件,能可靠保证发射筒盖的正常开启.

In order to study the method of opening the pre-and-post fragile cover by gas pressure when the missile was launched, the numerical simulation and experiment for a certain missile＇s opening cover technology were carried out by computational fluid technology and experiment method. The 2D model of missile and firing tube, as well as 3D model, was built. The research shows that the post-fragile-cover of the missile with pre-and-post fragile cover technology was cracked directly by the rocket jet flow, and the pre-fragile-cover was opened by the disturbance wave. Through configuring the pre-and-post fragile cover＇s opening condition reasonably, the launcher cover can open normally.