摘要
为全面研究GATo-3推进剂的热安全性,采用自行设计的实验装置,进行了不同恒温环境下的热自燃实验,通过测量温度的变化和热自燃延滞期,分析了其热自燃过程特性。同时,采用仿真软件Fluent建立GATo-3推进剂的热自燃实验模型,完成验证并研究了热自燃过程中样品的内部温度分布、点火位置变化和临界温度等。结果表明,GATo-3推进剂的热自燃过程可分为热升温阶段、恒温分解阶段和自热加速升温阶段。温度升高,热自燃延滞期缩短,反应程度更剧烈,点火区域从中心位置向外移动。实验药量下,GATo-3推进剂热自燃的临界温度为83℃。
To study thermal safety of GATo-3 propellant roundly, the thermal self-ignition experiment was carried out by a kind of self-constructed test device.The experimental phenomenon and process were analyzed, through measuring the self-ignition temper- ature and time to ignition of GATo-3 propellant at different temperature.GATo-3 propellant thermal self-ignition reaction model was established by using the simulation software Fluent.The temperature changes in the process of thermal self-ignition,ignition area and the critical temperature were simulated.The results show that according to the changes of the internal temperature of GATo-3 propel- lant, the thermal self-ignition process is divided into three stages including temperature rise with heat, isothermal decomposition and the self-heating.With the higher temperature, the response time is short and the reaction is more intense.The thermal self-ignition critical temperature of GATo-3 propellant is 83℃ at the experimental dose.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2016年第2期207-212,共6页
Journal of Solid Rocket Technology
关键词
改性双基推进剂
GATo-3推进剂
热自燃
数值模拟
modified double-base propellant
GATo-3 propellant
thermal self-ignition
numerical simulation
