采用差示扫描量热仪DSC和绝热加速量热仪ARC,对比研究了双基推进剂SF、改性双基推进剂GHQ和单质RDX的热分解过程,并分析评估了GHQ推进剂的热危害性.DSC实验结果表明:GHQ推进剂起始分解温度为182.4℃,热分解明显分为双基组分和RDX分解两个过程,分解峰温为202.2℃和240.4℃,分别与双基推进剂SF、单质RDX分解峰温接近,说明双基组分与RDX混合后作用不激烈.ARC实验结果表明:GHQ推进剂在最危险状态(即绝热条件)下的起始分解温度为135.3℃,绝热温升为1197.5℃,tMR为15.9min,单位质量产生气体最大压力为15.8MPa·g-1.研究结果表明:添加RDX后,GHQ推进剂发生热自燃可能性较双基推进剂SF稍有提高,热危害性大大增强.%A comparative study of the decomposition process of SF propellant and modified double-base propellant GHQ , as well as pure RDX was conducted, and thermal analysis and evaluation were obtained by differential scanning calorimetry (DSC)and adiabatic accelerating rate calorimeter(ARC). DSC experimental results show that GHQ propellant initial decomposition temperature is 182.4℃, the thermal decomposition is divided into double-base component and RDX decomposition process. The decomposition peak temperature of double-base and RDX component is 202.2 and 240.4℃, and they are close to SF propellant, pure RDX decomposition peak temperature. ARC experimental results show that the initial decomposition temperature of GHQ propellant in the most dangerous adiabatic condition is 135.3℃, the adiabatic temperature rise is 1197.5℃,tMR is 15.9min, and the maximum pressure produced by unit mass is 15.8MPa?g-1. The studies have showed that the thermal explosion feasibility and the degree of the spontaneous combustion hazard of GHQ propellant are higher than that of SF propellant.
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