Influence of cold launch bullet body deflection on the force and thermal environment of launch vehicles
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摘要:
针对冷发射过程弹体偏转不同角度后车载发射装置力热环境复杂恶劣的问题，基于嵌套动网格技术，采用Navier-Stokes组分运输方程、RNG
k -ε 模型建立弹体点火后飞行过程中燃气射流流动模型并开展数值模拟研究。首先，通过与相关实验结果对比，验证计算方法的有效性；在此基础上分别对比分析不同偏转角度下燃气射流流场结果、车体部件表面温压分布、监测点数值曲线探究弹体偏转对发射装置力热环境影响。研究表明：随着弹体倾斜角度的增加，发射筒口处的引射现象更为剧烈；车体部件壁面高温高压区从车体中部壁面向车体尾部方向偏移后又向车体头部方向偏移，车架、底盘等部件尾部壁面温度压强峰值先增加后减小，中部壁面峰值持续增加。随着倾斜角度的改变，发射筒筒口温度峰值最高升高20%，压强峰值最高升高450%，而车架、底盘等部件温度、压强峰值升高约50%。Abstract:In response to the complex and harsh force-thermal environment of the vehicle-mounted launch system during the cold launch projectile deviation at different angles, numerical simulation study was conducted based on nested grid technology, by utilizing the Navier-Stokes component transport equations and RNG
k -ε model to establish a dynamic flight gas jet model after the ignition of the projectile. Firstly, the accuracy of the calculation method was verified by comparing it with relevant experimental results. Based on this, a comparative analysis was conducted on the gas jet flow field results, the temperature and pressure distributions on the surface of vehicle components, and numerical curves at monitoring points to explore the influence of projectile deflection on the force-thermal environment of the launch system. The research demonstrated that as the inclination angle of the projectile increased, the ejection phenomenon at the muzzle of the launch tube became more pronounced. The high-temperature and high-pressure region on the surface of vehicle components moved from the middle section of the components towards the rear of the vehicle and then continued to move towards the front. The temperature and pressure peak values on the rear wall surface of the chassis and undercarriage components initially increased and then decreased. In contrast, the peak value on the middle wall surface continued to grow. With changes in the inclination angle, the temperature peak value at the mouth of the launch tube increased by up to 20%, and the pressure peak value increased by up to 450%. Meanwhile, the temperature and pressure peak values of the chassis, undercarriage, and other components increased by approximately 50%.-
Key words:
- cold launch /
- bullet body deflection /
- force and thermal environment /
- overset grid /
- gas jet
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图 8 实验结果与本文计算结果流场对比图
Figure 8. Comparison of experimental results with the flow field calculated in this paper
图 9 实验数据与本文计算结果对比图
Figure 9. Comparison between experimental data and calculation results in this article
图 10 过车体中心对称面马赫数分布
Figure 10. Mach number distribution on the symmetrical plane passing through the center of the vehicle body
图 11 过对称面及发射筒筒口和中心截面温度分布
Figure 11. Temperature distribution of the over symmetric plane and the mouth and center section of the launch cylinder
图 12 车架表面温度分布（t=0.64 s）
Figure 12. Temperature distribution on the surface of the vehicle frame （t=0.64 s）
图 13 底盘表面温度分布（t=0.64 s）
Figure 13. Surface temperature distribution of chassis （t=0.64 s）
图 14 车架表面压强分布（t=0.64 s）
Figure 14. Pressure distribution on the surface of the vehicle frame （t=0.64 s）
图 15 底盘表面压强分布（t=0.64 s）
Figure 15. Pressure distribution on the chassis surface （t=0.64 s）
表 1 燃气热力学参数
Table 1. Thermodynamic parameters of gas
流动参数 数值 总温/K 3 621 比热容/（J/（kg·K）） 2050.43 比热比 1.15 出口速度/（m/s） 2860 气体分子量 18.1 黏度/10−5 （N/（s·m2）） 1.94 导热系数/（W/（m·K）） 0.029 
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