摘要
在近空间高超声速飞行器飞行时间长、马赫数不断增加的发展趋势下,热防护与轻量化的矛盾越来越突出。基于此,开展了热解气体燃烧对炭化复合材料表面烧蚀影响的相关数值模拟研究,并与风洞试验结果进行了对比。结果表明:热解气体的燃烧可降低炭化复合材料表面的烧蚀厚度,并且随着气动热的增加,热解气体燃烧对材料表面碳的保护作用越来越明显。研究成果可为下一代近空间高超声速飞行器热防护系统的优化设计提供技术支撑。
Under the trend of longer flight time and higher Mach number for near space hypersonic vehicle,contradiction between thermal protection effect and lightweight is more prominent.Thus,numerical simulation of influence of pyrolysis gases combustion on surface ablation of charring material was carried out and the result was compared with that of arcjet test.Numerical results show that pyrolysis gases combustion can lead to the reduction in thickness of the ablation layer.With the increase in aerodynamic heat,protective effect of pyrolysis gases combustion on surface char is more apparent.This study can provide technical support for the optimization design of thermal protection system of the next generation near space hypersonic vehicle.
作者
郭瑾
黄海明
GUO Jin;HUANG Haiming(School of Civil Engineering,Beijing Jiaotong University,Beijing 100044,China)
出处
《中国空间科学技术》
EI
CSCD
北大核心
2020年第6期41-47,共7页
Chinese Space Science and Technology
基金
中央高校基本科研业务费专项资金资助项目(2019YJS127)。
关键词
热解气体燃烧
炭化复合材料
高超声速飞行器
表面烧蚀
气动热
pyrolysis gases combustion
charring material
hypersonic vehicle
surface ablation
aerodynamic heat
