摘要
采用有2个流速试验段的烧蚀试验发动机在双基推进剂和含Al 10%复合推进剂燃气环境下对EPDM绝热材料进行烧蚀试验,分析了压强、燃气组分和速度等因素对EPDM绝热材料烧蚀特性和炭化层微观结构的影响规律。研究表明,EPDM绝热材料炭化率和质量烧蚀率随着燃气速度和燃烧室压强的增加而增大;在燃气温度、燃烧室压强和燃气速度接近的条件下,含Al 10%复合推进剂燃气环境下的炭化率是双基推进剂燃气环境下的2倍;EPDM绝热材料炭化层的结构呈现一种致密/疏松的多孔结构,表面存在一层致密层。烧蚀模型中炭化层物理模型可用非均质可渗透多孔介质描述。
A solid rocket motor with two different gas velocity experiment segments for ablation test was used to conducted experimental investigation on properties of charring layer of EPDM at different chamber pressure and in combustion gas environments of double-base propellant and 10% aluminum-containing composite propellant.The charring layer of EPDM insulator were analyzed by means of SEM and EDS.The results show charring rate and mass loss rate of EPDM are increased with the increasing of chamber pressure and gas velocity.Under the condition of approximate gas temperature,pressure and velocity,the charring rate of the insulation material in combustion gas environment of 10% aluminum-containing composite propellants is twice that of double-base propellant.The charring layer is porous/compact structure with a compact surface.The physical model of the charring layer can be described as a nonhomogeneous,permeable and porous media.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2010年第5期586-589,593,共5页
Journal of Solid Rocket Technology
作者简介
陈剑（1973-），男，工程师，主要从事航空宇航推进理论与工程研究。
