摘要
火箭弹发射时,火箭弹尾部燃气射流会形成波系结构复杂的燃气冲击流场。为分析燃气对发射平台的冲击,基于有限体积法,采用了Realizable k-ω模型,耦合了火箭弹的内弹道过程,建立火箭弹尾部燃气射流三维的数值模拟模型。以安装在发射平台上的火箭发射器为例,分别在火箭弹高角为15°和28°工况下射击时,通过尾部喷出的火药气体流场进行计算,分析尾部火药燃气射流对平台壁面的冲击作用,得到在不同高角射击下不同时刻的气流速度场以及对发射平台壁面的冲击压力,绘制出对壁面的压力曲线图,并且对壁面压力的冲击变化过程做出了分析研究并将其结果与试验对照,验证了数值模拟结果的准确性,在高角为28°时,相较与高角为15°其火药燃气射流对平台壁面的冲击作用明显更大。
When a rocket is launched,the gas jet at the tail will form a gas impact flow field with a complex wave structure.In order to analyze the impact of gas on the launching platform,a three-dimensional numerical simulation model of the gas jet in the rocket tail was established based on the finite volume method,the Realizable k-ωmodel and the interior ballistic process.Taking the rocket launcher installed on the launching platform as an example,when the rocket was fired at 15°and 28°respectively,the propellant gas flow field emitted from the tail was calculated to analyze the impact of the jet on the wall of the platform,and the jet velocity field at different times and elevating angles was obtained,as well as the impact pressure on the wall.Then a pressure curve was drawn and the impact change process was analyzed.The results were compared with the experiment results to verify the accuracy of the numerical simulation results.The impact effect of the propellant gas jet on the wall is obviously larger when the elevating angle is 28°compared with the elevating angle of 15°.
作者
刘宇豪
曲普
李强
李景龙
LIU Yuhao;QU Pu;LI Qiang;LI Jinglong(School of Mechanical&Electrical Engineering,North University of China,Taiyuan 030051,Shanxi,China)
出处
《火炮发射与控制学报》
北大核心
2024年第3期38-44,69,共8页
Journal of Gun Launch & Control
基金
航空科学基金(2019290U0003)。
关键词
燃气射流
发射平台
内弹道
火箭弹高角
气流速度场
冲击压力
gas jet
launching platform
interior ballistics
rocket high angle
jet velocity field
impact pressure
