Study on thermal safety of RDX CMDB

DOI:	10.11809/bqzbgcxb2023.02.026
Keywords:	modified double base propellant; thermal decomposition characteristic; thermal safety; explosive; thermodynamic analysis
Abstract:	In order to study thermal decomposition and thermal safety characteristics of RDX CMDB, this paper uses a micro calorimeter to carry out linear heating experiments. The thermal adiabatic induction period (TMR ad ) and self accelerating decomposition temperature (SADT) of RDX CMDB are obtained through dynamics calculation by combining Kissinger method, Friedman method and heat balance equations. The results show that the initial decomposition temperature, the maximum decomposition temperature and the decomposition completion temperature of RDX CMDB propellant all move to high temperatures with an increase of the heating rate, and the average decomposition heat is 3 463.8 J·g -1 . As the heating rate increases, the initial decomposition temperature after decoupling advances, and the decomposition enthalpies are 468.3 J·g -1 and 1 348.7 J·g -1 respectively. The kinetic model shows that the RDX CMDB propellant has different reactions in different reaction stages. When the adiabatic induction periods are 2.0, 4.0, 8.0 and 24.0 h, the corresponding adiabatic temperatures are 132.4, 122.9, 113.9 and 100.6 ℃ respectively. When the packing mass is 5.0, 15.0, 25.0, 50.0 and 100.0 kg, the self accelerating decomposition temperatures are 91.0, 88.0, 87.0, 84.0 and 82.0 ℃ respectively. With an increase of packaging mass, it is difficult to release heat from the thermal decomposition of RDX CMDB,, and its safety decreases.
Published:	2023-02-28
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