基于CFD-FASTRAN的小型发射筒激波开盖过程仿真分析

王启凡; 安超; 魏广威; 秦会国

doi:10.15892/j.cnki.djzdxb.2025.02.010

弹箭与制导学报 >

2025 , Vol. 45 >Issue 2: 199 - 207

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2025.02.010

基于CFD-FASTRAN的小型发射筒激波开盖过程仿真分析

王启凡 ^,¹ ,
安超 ² ,
魏广威 ¹ ,
秦会国 ¹

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¹ 北京机械设备研究所, 北京 100854
² 空军装备部驻北京地区第一军事代表室, 北京 100854

王启凡(1993—), 男, 工程师, 硕士。E-mail: 1162885549@qq.com

收稿日期: 2024-07-08

网络出版日期: 2025-05-15

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CFD-FASTRAN-based Simulation and Analysis of Small Launch Tube Shock Wave Opening Process

WANG Qifan ^,¹ ,
AN Chao ² ,
WEI Guangwei ¹ ,
QIN Huiguo ¹

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¹ Beijing Institute of Mechanical Equipment, Beijing 100854, China
² Office of the First Military Representative of the Air Force Equipment Department in Beijing, Beijing 100854, China

Received date: 2024-07-08

Online published: 2025-05-15

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摘要

为研究小型发射筒热发射激波开盖过程, 通过CFD-FASTRAN气动分析软件对其过程进行数值仿真计算。根据计算结果分析给出了小型发射筒热发射激波开盖过程中主要部件表面温度、压力所受燃气激波影响的变化过程。创新性通过CFD-FASTRAN气动分析软件对小型发射筒热发射激波开盖全过程进行了分析, 并首次系统性分析了喷管与后盖距离以及喷管扩张角度对激波开盖过程的影响。结果表明, 后盖受到燃气射流影响压力由边缘向中心减小, 温度由边缘向中心增大;燃气流反射激波沿发射筒轴向向弹头方向运动, 发射筒壁面压力、温度随激波运动方向逐渐减小;前盖受到燃气激波影响温度、压力由边缘向中心减弱;弹体喷管出口与后盖的距离增大、喷管扩张角度增大均有利于增强激波反射到前盖的总能量, 同时可以缩短激波开盖的时间。计算模拟方法可为采用热发射激波开盖的小型发射筒前后盖强度设计、结构设计等提供参考依据。

关键词： CFD-FASTRAN; 发射筒; 激波; 计算流体; 燃气射流

本文引用格式

王启凡 , 安超 , 魏广威 , 秦会国 . 基于CFD-FASTRAN的小型发射筒激波开盖过程仿真分析[J]. 弹箭与制导学报, 2025 , 45(2) : 199 -207 . DOI: 10.15892/j.cnki.djzdxb.2025.02.010

Abstract

In order to study the hot launch shock wave opening process of small launcher, a numerical simulation of the process is carried out by using CFD-FASTRAN aerodynamic analysis software. According to the calculation results analysis, it gives the changing process of surface temperature and pressure of main components affects by gas shock wave in the process of hot launch shock wave opening of small launch tube. The whole process of hot launch shock cap opening is analyzed by using CFD-FASTRAN pneumatic analysis software innovatively, and the influence of the distance between nozzle and back cap and the expansion angle of nozzle on the shock cap opening process is systematically analyzed for the first time. The results show that the pressure decreases from edge to center and the temperature increases from edge to center under the influence of gas jet. The shock wave reflected by the gas flow moves along the axis of the launch tube towards the warhead, and the pressure and temperature on the wall of the launch tube gradually decrease with the direction of the shock wave. The temperature and pressure of the front cover are weakened from edge to center by the gas shock wave influence. The increase of the distance between the nozzle outlet and the rear cover and the increase of the expansion angle of the nozzle can enhance the total energy reflected by the shock wave to the front cover, and shorten the opening time of the shock wave. The calculation and simulation method can provide a reference for the strength design and structure design of the front and back covers of the small launch tube with hot launch shock wave.

Key words： CFD-FASTRAN; launch tube; shock wave; computational fluid; gas jet

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