摘要
为了深入研究以液体运载火箭动力系统构成发射平台的燃气冲击流场,采用数值模拟的方法对运载火箭起飞阶段的流场和发射平台热环境展开研究。基于三维多组分可压缩Navier-Stokes方程、Realizable k-ε两方程湍流模型、二阶迎风TVD格式离散,构建了双喷管运载火箭发射阶段的燃气射流模型。结果表明,随着火箭起飞高度的增加,燃气射流膨胀角度逐渐增大,之间相互作用增强,射流对发射平台的冲击呈现出先上升后下降的趋势,0 m处的冲击最小,20 m处的冲击最大。支撑臂表面的峰值温度最高为706 K,比最低工况下大约增加了127%。盖板表面的温度和压强前期随着火箭起飞高度的增加而升高,后期随着起飞高度的增加而降低。该文的研究方法为运载火箭发射平台的安全设计提供了参考。
In order to deeply study the gas impingement flow field of a launch platform composed of a liquid launch vehicle power system,the numerical simulation method was used to study the flow field and the thermal environment of the launch platform during the launch phase of the launch vehicle.Based on three-dimensional multi-component compressible Navier-Stokes equations,the Realizable k-εtwo-equation turbulence model and the second-order upwind total variation diminishing(TVD)format discretization,the gas jet model of the launch phase of the dual-nozzle launch vehicle is conducted.The results show that with the increase of the rocket take-off altitude,the expansion angle of the gas jet increases gradually,and the interaction between them is enhanced.The impact of the jet on the launch platform shows a trend of first rising and then falling,with the impact at 0 m being the smallest,and the impact at 20 m being the largest.The maximum peak temperature of the support arm surface is 706 K,which is about 127%higher than that under the lowest working condition.The temperature and pressure of the cover plate surface increase with the increase of the rocket take-off altitude in the early stage,and decrease with the increase of the rocket take-off altitude in the later stage.The research method in this paper provides a reference for the safety design of the launch platform.
作者
赵晨耕
王辉
孙中一
乐贵高
Zhao Chengeng;Wang Hui;Sun Zhongyi;Le Guigao(School of Mechanical Engineering,Nanjing University of Science and Technology,Nanjing 210094,China;Chengdu Aerospace Wanxin Science and Technology Co.,Ltd.,Chengdu 610100,China)
出处
《南京理工大学学报》
CAS
CSCD
北大核心
2024年第3期253-261,共9页
Journal of Nanjing University of Science and Technology
关键词
发射平台
燃气射流
支撑臂
盖板
热环境
launch platform
gas jet
support arm
cover plate
thermal environment
