导弹弹射气体冲击载荷实验与仿真研究

Experimental and simulation study on missile ejection gas impact load

设计一套模拟发射筒内建压过程的装置,使之能够模拟不同建压速度、不同终值压强时的发射筒内建压过程,进而对导弹弹射过程中导弹尾罩和其他结构受到的气体冲击载荷进行地面冷实验。分别对四种不同初始条件下的建压过程进行了实验,并对一种情况进行了数值模拟仿真。结果显示,实验设备通过调节柱塞两侧初始压力差和高压气缸初始压力,可以实现对不同建压速率、不同终值压强的模拟;在建压过程中模拟发射筒内存在明显涡流,尾罩中间部位受压更大,变形时间相较于升压时间存在明显滞后。

A set of device was designed to simulate the built-up pressure process of the launcher,so that it could simulate the built-up pressure process of launcher at different build-up speed and different final pressure.Furthermore,the ground cold experiments were carried out on the gas impact load on the missile tail cover and other structures during missile ejection.Experiments were carried out on four different initial conditions,and numerical simulation was carried out on one case.The results show that the experimental equipment can simulate different pressure building rates and different final pressure by adjusting the initial pressure difference between the two sides of the plunger and the initial pressure of the high-pressure cylinder.During the process of pressure build-up,there are obvious eddies in the simulated launcher.The pressure in the middle part of the tail hood is greater,and the deformation time lags behind the pressure rising time.