改黑铜推进剂的热分解动力学

Thermal Decomposition Kinetics of RDX-based CMDB Propellant

基于热分析动力学理论,用热重法(TG)研究了改黑铜推进剂在不同升温速率(2.5、5、7.5、10K/min)下的热分解过程。采用Ozawa法、KSA法和Coats-Redfern法计算了热分解反应的动力学参数。结果表明,改黑铜推进剂的热分解过程分为两个阶段:第Ⅰ反应阶段反应机理服从一级Mample法则,动力学参数为E=83.5kJ/mol,A=108.46s-1,动力学方程为dα/dt=108.46(1-α)exp(1.00×104/T);第Ⅱ反应阶段反应机理服从四级化学反应,动力学参数为E=219.6kJ/mol,A=1020.07s-1,动力学方程为dα/dt=1020.07(1-α)4exp(2.66×104/T)。

Based on the theory of thermal analysis kinetics,the thermal decomposition process of RDX-based CMDB propellant was investigated by thermogravimetry （TG） at four different heating rates of 2.5,5,7.5 and 10 K/min.The kinetic parameters of thermal decomposition reaction of RDX-based CMDB propellant were calculated by Ozawa method,KSA method and Coats-Redfern method.The results indicate that there are two reaction stages in the decomposition process of RDX-based CMDB propellant.The decomposition reaction mechanism of stage Ⅰ obeys Mample single-file law with n=1,the kinetic parameters are determined as：E=83.5 kJ/mol,A=108.46s-1,and the kinetic equations can be expressed as dα/dt=108.46 （1-α）exp（1.00 × 104/T）.The decomposition reaction mechanism of stage 11 obeys four-steps chemical reaction rule,the kinetic parameters are determined as：E=219.6 kJ/mol,A=1020.07s-1,and the kinetic equations can be expressed as dα/dt=1020.07 （1-α）4 exp（2.66 × 104/T）.