箱式发射装置迎气面动态效应及试验研究

Dynamic Effects and Experimental Study on the WindwardSide of a Box Launcher

以某运载火箭发射系统为工程背景,根据火箭弹发射过程流场流动特性,利用计算流体力学方法建立火箭发射装置发射流场分析模型。对发射箱迎气面上流场分布进行数值模拟,获得燃气射流对发射管位邻管的流场压强。通过实物样机的实弹射击试验获得该发射装置的振动特性和邻管压强测试数据,邻管流场压强数值分析结果与试验情况吻合良好,验证了仿真分析的正确性和有效性;试验获取的发射装置在不同弹种发射时的振动加速度规律基本可信,发射过程发射装置具有显著衰减效应,发射装置振动完全衰减的最大时间小于射击间隔,表明了发射装置结构设计合理,满足工程使用要求,为相关武器装备的仿真分析和实验测试提供了参考和理论依据。

Taking a launch vehicle system as the engineering background,a launch flow field analysis model of the rocket launcher was established by using computational fluid dynamics methods based on flow field characteristics during rocket launch.The flow field distribution on the windward side of the launch box is simulated numerically and the pressure of the gas jet on the adjacent pipe is obtained.The vibration characteristics of the launcher and the pressure experiment test data of the tube adjacent to the launch tube are obtained through the live fire test of the prototype.The numerical analysis results of the pressure in the adjacent tube flow field are in good agreement with the test results,which verifies the correctness and effectiveness of the simulation analysis.The law governing vibration accelerations,obtained experimentally by firing different rockets using the launcher,is by and large credible.The launcher showed significant attenuating effects during the launching process.The maximum time for the vibration of the launcher to be fully attenuated is less than the firing interval.It shows the launcher is well configured and meets the requirements of engineering application.The study provides references and a theoretical basis for simulation analyses and experimental tests of similar weapons and equipment.