摘要
研究了固体火箭发动机燃烧室绝热材料烧蚀实验发动机的特点以及烧蚀率和炭化层的表征及测量方法。在分析炭化层多孔结构特点的基础上,获得了由电镜照片处理得到特征面孔隙率的经验阈值,推导获得了由面孔隙率向体孔隙率转化的修正系数,从而给出了绝热材料烧蚀炭化层微区孔隙率的处理方法,为烧蚀机理分析和烧蚀模型建立提供数据支持。
The characteristics of ablation experiment engine for solid rocket motor combustion chamber in- sulator and the representation and measurement method for ablation rate and carbon layer were clarified. Based on the analysis of carbon layer porous structure＇ s characteristics, the experience threshold Used for converting from SEM photo to face porosity was obtained and the correction coefficient used for converting from face porosity to bulk porosity was derived. Thus the method of insulator carbon layer microcosmic porosity processing was proposed. The results provide data support for ablation mechanism analysis and ablation model establishment.
出处
《四川兵工学报》
CAS
2015年第4期120-123,共4页
Journal of Sichuan Ordnance
基金
西安航空学院校级科研基金"孔隙结构对炭化层内流场影响的数值研究"(13XP26)
