模拟固冲条件下绝热材料烧蚀实验及影响规律研究  

Experimental investigation of insulator material under conditions simulating solid propellant ramjet

作　　者：严聪[1] 刘洋[1] 孙得川[1] 何国强[1] 孙翔宇[2] 胡淑芳[2] 

机构地区：[1]西北工业大学燃烧流动和热结构国家级重点实验室,西安710072 [2]中国航天科工集团公司六院,呼和浩特010000

出　　处：《固体火箭技术》2011年第4期506-509,513,共5页Journal of Solid Rocket Technology

基　　金：国家973项目

摘　　要：在已有的富氧条件下绝热材料烧蚀系统的基础上,提取了典型固冲发动机补燃室内绝热材料的烧蚀边界参数,改进了实验系统的工作参数调节范围,针对3种不同配方的硅橡胶绝热材料进行了筛选,并对影响规律进行研究。实验分别获得了3种材料的最大炭化烧蚀率,筛选出了抗烧蚀能力较强的绝热材料。研究结果表明,在此实验条件下,3种材料的烧蚀率由压强和富氧度共同主导,烧蚀率均随压强和富氧度的增加而增加;但3种绝热材料烧蚀率随富氧度的变化趋势有一定差别,当富氧小于10%时,采用高硅氧纤维和炭纤维的973S-1材料的烧蚀率小于其他2种材料,当富氧度继续增加时,973S-1材料的烧蚀率要大于完全采用高硅氧纤维的973S-4材料,而完全采用炭纤维的973S-3材料烧蚀性能最差。实验结果为固冲发动机补燃室内绝热材料的配方设计提供了依据。Utilizing the existing ablation experimental system for the insulator material under oxygen-rich conditions,some ablation boundary parameters were extracted for afterburner insulator material of typical solid ramjet,and operation parameter＇s range in the experiment system was improved.Three formula of silicone rubber insulator ablation materials were selected and investigated,and the maximal charring ablation rate was obtained respectively.The results show that the charring ablation rate of three kinds of insulator materials is dominant by oxygen content and combustor pressure;the higher the oxygen content and combustor pressure is,the higher the carburization ablation rate;but the influence trend of three kinds of insulator materials are different,and charring ablation rate of 973S-1 is less than those of other insulators when the oxygen content is less than 10%;the charring ablation rate of 973S-1 is more than those of other insulators when the oxygen content is more than 10%.

关 键 词：固体冲压发动机 富氧环境 绝热材料 实验研究 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]