GHQ推进剂的绝热分解特性  

Adiabatic Decomposition Properties of GHQ Propellant

作　　者：曲国庆[1] 江劲勇[1,2] 路桂娥[1,2] 贾昊楠[1,2] 葛强[1,2] 

机构地区：[1]军械工程学院弹药工程系,河北石家庄050003 [2]军械技术研究所,河北石家庄050000

出　　处：《装甲兵工程学院学报》2017年第2期80-83,共4页Journal of Academy of Armored Force Engineering

基　　金：军队科研计划项目

摘　　要：为研究GHQ推进剂的热分解性、热稳定性和热安全性,利用绝热加速量热仪(Accelerating Rate Calorimeter,ARC)测试了GHQ推进剂的绝热分解过程,得到了温度、压力实时变化曲线,最大反应速率到达时间(Time to the Maximum Rate,TMR)曲线,以及温升速率、压力随温度变化曲线。通过热惰性因子对样品在最危险状态(即绝热条件)下的起始分解温度、起始温升速率、最大温升速率、绝热温升和反应热进行了修正,并与GHT-1A推进剂进行了比较,结果表明:GHQ推进剂热稳定性低于GHT-1A推进剂,但具有良好的热安全性。To study the thermal decomposition property,thermal stability and thermal safety of GHQ propellant,adiabatic decomposition process of GHQ propellant is studied by Accelerating Rate Calorimeter（ ARC）. Temperature and pressure versus time curves,Time to the Maximum Rate（ TMR） curves,temperature rise rate and pressure versus temperature curves are obtained. Initial decomposition temperature,initial temperature rise rate,maximum temperature rise rate,adiabatic temperature rise and reaction heat are corrected through thermal inertia factor. GHQ propellant is compared with GHT-1A propellant in the most dangerous state when the sample is starting under adiabatic condition. The results show that the thermal stability of GHQ propellant is lower than that of GHT-1A propellant,but has better thermal safety.

关 键 词：GHQ推进剂 热惰性因子 绝热分解 动力学参数 

分 类 号：TJ55[兵器科学与技术—军事化学与烟火技术] TJ714