CAJ | 학술논문

采用热重分析仪( TG)、差示扫描量热仪( DSC)、微量热仪(μRC)和加速量热仪( ARC)研究了一种国内自行研制的RDX含量接近50%的改性双基推进剂( GHT-1A)的热分解行为和热危险性. TG和DSC结果表明,GHT-1A的放热分解过程可分为2个阶段,表观活化能(Ea)和指前因子(A)按阶段分别为:Ea1=148.4 kJ mol-1,lgA1=14.8 s-1;Ea2=175.1 kJ mol-1 ,lgA2=16.5 s-1. 2个阶段的化学反应机理函数均遵循Avrami-Erofeev方程. 通过μRC研究了GHT-1A的比热容随温度的变化规律,结合DSC实验结果,计算得到了GHT-1A热爆炸临界温度为212.0 ℃,绝热至爆时间tad为22.7 min. ARC实验揭示了GHT-1A的绝热分解行为,并通过对实验数据进行热惰性因子修正,获得了大量绝热特性参数. 由ARC实验得到的tad比由DSC计算得到的tad短8.9 min. 由绝热反应动力学计算得到GHT-1A的TD24为120.8 ℃. 基于以上结果,对GHT-1A的热危险性进行了初步的分析.
채용열중분석의( TG)、차시소묘량열의( DSC)、미량열의(μRC)화가속량열의( ARC)연구료일충국내자행연제적RDX함량접근50%적개성쌍기추진제( GHT-1A)적열분해행위화열위험성. TG화DSC결과표명,GHT-1A적방열분해과정가분위2개계단,표관활화능(Ea)화지전인자(A)안계단분별위:Ea1=148.4 kJ mol-1,lgA1=14.8 s-1;Ea2=175.1 kJ mol-1 ,lgA2=16.5 s-1. 2개계단적화학반응궤리함수균준순Avrami-Erofeev방정. 통과μRC연구료GHT-1A적비열용수온도적변화규률,결합DSC실험결과,계산득도료GHT-1A열폭작림계온도위212.0 ℃,절열지폭시간tad위22.7 min. ARC실험게시료GHT-1A적절열분해행위,병통과대실험수거진행열타성인자수정,획득료대량절열특성삼수. 유ARC실험득도적tad비유DSC계산득도적tad단8.9 min. 유절열반응동역학계산득도GHT-1A적TD24위120.8 ℃. 기우이상결과,대GHT-1A적열위험성진행료초보적분석.
To evaluate thermal decomposition behaviors and thermal hazard of the composite modified double base( CMDB) pro-pellant with higher RDX content,a domestic developed CMDB propellant with approximate 50% RDX( named GHT-1A) ,was inves-tigated by thermogravimetry(TG),differential scanning calorimetry(DSC),micro reaction calorimetry(μRC)and accelerating rate calorimetry(ARC).TG and DSC results show the exothermic decomposition process of GHT-1A can be divided into two stages.The values of the apparent activation energy( Ea ) and pre-exponential constant( A) of the two stages are:Ea1=148.4 kJ mol-1 ,lgA1=14.8 s-1,and Ea2=175.1 kJ mol-1,lgA2=16.5 s-1.The chemical reaction mechanisms both obey the Avrami-Erofeev equation.The critical temperature of the thermal explosion of GHT-1A derived from DSC data is 212.0℃.The specific heat capacity of GHT-1A was de-termined by μRC.The calculation results show that the adiabatic time-to-explosion of GHT-1A is 22.7 min.ARC results reveal the adiabatic decomposition behaviors of GHT-1A,and a mass of adiabatic parameters were derived directly or by inertia factor modif-ying.The adiabatic time-to-explosion obtained by ARC is 8.9 min shorter than the front.TD24 estimated by adiabatic reaction kinetics is 120.8 ℃.Based on these results,the thermal hazard of the CMDB propellant with high content of RDX was analyzed preliminarily.