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<p>To compare the thermal safety of double-base propellants and two modified double-base propellants (RDX/HMX-CMDB) containing equal amounts of hexogen (RDX) and octogen (HMX), the thermolysis and thermogravimetric behavior of these propellants were evaluated using differential scanning calorimetry (DSC) and thermogravimetry (TG) in this work. Based on the experimental data, multiple kinetic methods, including Kissinger, Ozawa, KAS, and Friedman, together with simulations using Thermal Safety Software (TSS), were employed to comprehensively evaluate the kinetic parameters and the time to maximum rate under adiabatic conditions (TMR<sub>ad</sub>) of the three samples. The findings indicated that adding RDX and HMX shifted the initial decomposition peak in the DSC curves of the double-base propellant to higher temperatures, and the thermal hysteresis induced by HMX became more prominent. At a heating rate of 10&#xa0;°C·min<sup>−1</sup>, the peak temperature increases from 204.84 to 205.39&#xa0;°C and 206.64&#xa0;°C for RDX-CMDB and HMX-CMDB propellants, respectively. Kinetic analysis using the Kissinger method shows that the apparent activation energies of RDX-CMDB and HMX-CMDB propellants are 213.49 and 214.33&#xa0;kJ·mol<sup>−1</sup>, respectively, both higher than the double-base propellant (199.06&#xa0;kJ·mol<sup>−1</sup>). The KAS and Friedman methods further reveal an increased complexity of the thermal decomposition process after the addition of RDX and HMX. TSS simulations indicated that the TD<sub>2</sub>, TD<sub>4</sub>, TD<sub>8</sub>, and TD<sub>24</sub> values for RDX-CMDB and HMX-CMDB propellants were greater than those of the double-base propellant. Both experimental and simulation results confirm that incorporating RDX and HMX effectively enhances the thermal safety of double-base propellants, with HMX exhibiting a more pronounced effect.</p>

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Comparative analysis of thermal decomposition and safety between double-base and RDX/HMX-CMDB propellants

  • 期刊论文

  • 发表日期：

    2026年4月1日

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  • Xuanshen Liu,
  • Runqing Liu,
  • Yang Zhang,
  • Siyu Xu,
  • Shuang Geng,
  • Chenshu Wu,
  • Qing He,
  • Shaoqian Cheng,
  • Wenzheng Xu,
  • Weiguo Cao

摘要

To compare the thermal safety of double-base propellants and two modified double-base propellants (RDX/HMX-CMDB) containing equal amounts of hexogen (RDX) and octogen (HMX), the thermolysis and thermogravimetric behavior of these propellants were evaluated using differential scanning calorimetry (DSC) and thermogravimetry (TG) in this work. Based on the experimental data, multiple kinetic methods, including Kissinger, Ozawa, KAS, and Friedman, together with simulations using Thermal Safety Software (TSS), were employed to comprehensively evaluate the kinetic parameters and the time to maximum rate under adiabatic conditions (TMRad) of the three samples. The findings indicated that adding RDX and HMX shifted the initial decomposition peak in the DSC curves of the double-base propellant to higher temperatures, and the thermal hysteresis induced by HMX became more prominent. At a heating rate of 10 °C·min−1, the peak temperature increases from 204.84 to 205.39 °C and 206.64 °C for RDX-CMDB and HMX-CMDB propellants, respectively. Kinetic analysis using the Kissinger method shows that the apparent activation energies of RDX-CMDB and HMX-CMDB propellants are 213.49 and 214.33 kJ·mol−1, respectively, both higher than the double-base propellant (199.06 kJ·mol−1). The KAS and Friedman methods further reveal an increased complexity of the thermal decomposition process after the addition of RDX and HMX. TSS simulations indicated that the TD2, TD4, TD8, and TD24 values for RDX-CMDB and HMX-CMDB propellants were greater than those of the double-base propellant. Both experimental and simulation results confirm that incorporating RDX and HMX effectively enhances the thermal safety of double-base propellants, with HMX exhibiting a more pronounced effect.